Entries |
Document | Title | Date |
20080202124 | Transition support system for combustion transition ducts for turbine engines - A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction. | 08-28-2008 |
20080216483 | Engine Assembly for Aircraft Comprising an Engine as Well as a Device for Locking Said Engine - An aircraft engine assembly including an engine and a mount device for the engine. The mount device can be positioned between a wing of the aircraft and the engine, and includes a rigid structure and a mechanism to mount the engine on the rigid structure, the mounting mechanism including a first attachment and a second attachment. The first attachment includes two side semi-attachments each fixed to a fan case of the engine, and the second attachment is fixed onto a forward part of a central case of the engine. | 09-11-2008 |
20080276621 | CATENARY MID-TURBINE FRAME DESIGN - An engine casing assembly having dual load transfer points includes a U-shaped mid-turbine frame, an engine casing, a plurality of dimples, a strut and a mounting apparatus. The engine casing has an exterior surface and an interior surface. A plurality dimples are formed in the engine casing so that U-shaped protrusions are formed in the interior surface and U-shaped indentions are formed in the exterior surface. A strut connects one U-shaped protrusion to the mid-turbine frame and a mounting apparatus located within an indention so that a load is transferred from the mid-turbine frame to the engine casing and the mounting apparatus. | 11-13-2008 |
20080282703 | INTERFACE BETWEEN A COMBUSTOR AND FUEL NOZZLE - A floating collar assembly is provided comprising a substantially flat floating collar trapped between a heat shield and a dome panel of the combustor. Axial engagement between the floating collar and the fuel nozzle is maintained via a nozzle cap mounted over the fuel nozzle tip. | 11-20-2008 |
20090049842 | ENCLOSURE FOR A GAS TURBINE AND METHOD FOR ENCLOSING THE SAME - Disclosed is an enclosure for a gas turbine, the enclosure including an enclosure section configured to partially enclose the gas turbine, and at least one other enclosure section, the at least one other enclosure section being configured to assemble with the enclosure section in a manner that associates the at least one other enclosure section with the enclosure section, wherein said at least one other enclosure section and said enclosure section are configured to substantially enclose the gas turbine when the at least one other enclosure section is associated with the enclosure section. | 02-26-2009 |
20090064684 | Systems Involving Inlet-Mounted Engine Controls - Systems involving inlet-mounted engine control components are provided. A representative system includes: a forward keep out zone defined by converging inner and outer walls of a nacelle; an aft keep out zone defined by a containment zone; and an engine control component, at least a portion of which is located between the forward keep out zone and the aft keep out zone, and between the inner and outer walls of the nacelle. | 03-12-2009 |
20090071167 | TURBOMACHINE, ESPECIALLY GAS TURBINE - A turbomachine with at least one combustion chamber and at least one turbine which lies downstream of it. The turbine has at least one support element and a lining element connected to the support element and formed as a heat shield. A gap sealed by means of a seal, is formed between the at least one combustion chamber and the turbine, an exchangeable insert is arranged in the gap on the end face on the support element and protects at least the support element against hot gases which penetrate into the gap, and against oxidation which is associated with it. | 03-19-2009 |
20090120101 | Organic Matrix Composite Components, Systems Using Such Components, and Methods for Manufacturing Such Components - Organic matrix composite components, systems using such components, and methods for manufacturing such components are provided. In this regard, a representative organic matrix composite component includes: an organic matrix composite; a layer of aluminum applied to the organic matrix composite; and a wear resistant coating applied to the aluminum layer. | 05-14-2009 |
20090145137 | TRANSITION DUCT ASSEMBLY - A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges. | 06-11-2009 |
20090193813 | COMBUSTION APPARATUS - A wall element for a combustion space, the wall element comprising a ceramic body, a support within the body, and attachment means extending from the support and protruding from the body for securing the ceramic body to a combustion space wall. | 08-06-2009 |
20090272123 | Gas Turbine Engine Systems and Related Methods Involving Thermally Isolated Retention - Gas turbine engine systems and related methods involving thermally isolated retention are provided. In this regard, a representative method for attaching a gas turbine engine component includes using a fastener, varying in diameter along a length thereof, to prevent a portion of a component from being crimped between surfaces to which the component is attached such that the component moves relative to the surfaces responsive to thermal cycling of a gas turbine engine of which the surfaces and the component are constituent parts. | 11-05-2009 |
20090293497 | GAS TURBINE ENGINE ASSEMBLY - A gas turbine engine assembly includes an inlet lip assembly, a fan containment case, and a front flange. The fan containment case surrounds a fan section and is positioned downstream from the inlet lip assembly. The front flange is mounted between the inlet lip assembly and the fan containment case and is positioned upstream from the fan section. | 12-03-2009 |
20090293498 | PIVOTING LINER HANGER - An example turbine engine assembly includes a first attachment structure secured to an engine casing or an engine liner. A second attachment structure is secured to the other of the engine casing or the engine liner. The assembly further includes a link having a rod portion extending longitudinally from a hemispherical end portion and terminating at a rod end portion. The hemispherical end portion is received within a recess defined by the first attachment structure. The rod end portion is secured relative to the second attachment structure to limit relative movement between the engine casing and the engine liner. | 12-03-2009 |
20090308078 | ENGINE MOUNTING APPARATUS - An engine mounting apparatus having a yoke carrier block and a main mount block, the yoke carrier block being connectable to the main mount block, the main mount block being connected to the engine by at least one engine attachment link for transferring loads from an engine in a normal load path during normal operation of the engine mounting arrangement, characterised in that the yoke carrier block is connected to a further engine attachment link independently of the main mount block, the further engine attachment link being unloaded during normal operation of the engine mounting arrangement and arranged to transfer loads from the engine in the event of a failure of one or more components in the normal load path. | 12-17-2009 |
20100000227 | AIR INTAKE FOR AN AIRCRAFT TURBINE ENGINE - According to the invention, the air intake ( | 01-07-2010 |
20100011780 | COMBUSTOR LINER SUPPORT AND SEAL ASSEMBLY - The invention is a combination that includes a gas turbine engine extending along an axis. The gas turbine engine includes an annular combustor with a combustor liner. The combination of the invention also includes a plurality of projections extending from the combustor liner and spaced from one another circumferentially about the axis. The combination of the invention also includes a free-standing ring disposed about the combustor liner and positioned adjacent to the plurality of projections along the axis. The plurality of projections engage a corresponding circumferentially-facing portion of the free-standing ring and circumferentially support the combustor liner while allowing relative radial displacement between the combustor liner and the free-standing ring. The combination of the invention also includes a rolling assembly operably disposed between the free-standing ring and the plurality of projections to reduce binding during the relative radial displacement. | 01-21-2010 |
20100031671 | INNER RING WITH INDEPENDENT THERMAL EXPANSION FOR MOUNTING GAS TURBINE FLOW PATH COMPONENTS - An inner mounting ring ( | 02-11-2010 |
20100031672 | GAS TURBINE - There is provided a gas turbine capable of improving the durability of a main shaft by absorbing the deformation of a casing due to heat and pressure and suppressing stresses acting on the main shaft. A link plate | 02-11-2010 |
20100031673 | CASING OF A GAS TURBINE ENGINE - A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side. | 02-11-2010 |
20100043448 | GAS TURBINE ENGINE COMBUSTOR AND METHOD FOR DELIVERING PURGE GAS INTO A COMBUSTION CHAMBER OF THE COMBUSTOR - In a gas turbine engine combustor and method for delivering purge gas thereto, a ferrule is generally coupled to the housing and moveable relative thereto. The ferrule has a primary opening through which a combustor component extends into a combustion chamber of the combustor. The ferrule further has a plurality of purge gas openings separate from and in transversely spaced relationship with the primary opening to allow purge gas to flow through the ferrule. In a first position of the ferrule at least one purge gas opening is blocked against the flow of purge gas therethrough and at least one other purge gas opening is unblocked against purge gas flow. In a second position of the ferrule at least one of the blocked purge gas openings of the first ferrule position is unblocked to permit the flow of purge gas therethrough. | 02-25-2010 |
20100043449 | DEVICE FOR ATTACHING A COMBUSTION CHAMBER - Turbomachine comprising an annular combustion chamber ( | 02-25-2010 |
20100089068 | Combustion liner damper - The present invention are directed towards a system and method for providing a way of reducing the vibrations and wear between mating components of a gas turbine combustor. The gas turbine combustor includes a flow sleeve having a plurality of liner stops and a combustion liner located radially within the flow sleeve. Spring dampers are positioned between the combustion liner and the flow sleeve to restrict the relative movement between the flow sleeve and the combustion liner and dampen vibrations at their assembly location. The spring dampers are capable of compressing to permit thermal growth between the combustion liner and flow sleeve. | 04-15-2010 |
20100095683 | Gas turbine engine and system for servicing a gas turbine engine - A gas turbine engine includes a compressor having first annular connection structure at a forward end portion of an air inlet housing of the compressor. The gas turbine engine may also include intake ducting having second annular connection structure adjacent a central passage of the intake ducting. The first annular connection structure and the second annular connection structure may form at least part of an interface between the air inlet housing and the intake ducting during operation of the gas turbine engine. The first and second annular connection structures may have shapes allowing the first annular connection structure to be moved through and beyond the second annular connection structure in a forward direction, the forward direction being opposite a direction of compressed air flow in the compressor during operation. | 04-22-2010 |
20100101232 | COMPLIANT METAL SUPPORT FOR CERAMIC COMBUSTOR LINER IN A GAS TURBINE ENGINE - A combustion system for an engine, such as a gas turbine engine is provided. The combustion system has a ceramic component, such as ceramic combustor liner, and at least one metal support component, such as a metal ring or a plurality of metal cones, for providing radial and axial support to the ceramic component. The at least one metal support component includes a structure, such as axial slots or radial slots, for minimizing stress and for increasing compliance of the metal support component with respect to the ceramic component. | 04-29-2010 |
20100107653 | NOZZLE TIP ASSEMBLY WITH SECONDARY RETENTION DEVICE - A nozzle tip assembly and method characterized by the use of a retention device including at least one tab that cooperates with a ledge for coupling a nozzle shroud to a nozzle adaptor. The retention device can be used as a secondary retention feature to prevent nozzle separation and/or to enable the fuel injector to be repaired without having to replace the entire assembly. The latter advantage is of particular benefit when there is damage during assembly or when the nozzle tip assembly is being overhauled. | 05-06-2010 |
20100126183 | CMC MIXER WITH STRUCTURAL OUTER COWLING - The invention relates to a mixer ( | 05-27-2010 |
20100126184 | COMBUSTION CHAMBER ARRANGEMENT FOR OPERATING A GAS TURBINE - A combustion chamber arrangement is described for operating a gas turbine, with a combustion chamber wall which encloses the combustion chamber space and in the region of the combustion chamber outlet encloses a flow passage for hot gases which develop inside the combustion chamber, has a combustion chamber wall edge which freely terminates in the axial flow direction of the hot gases. The combustion chamber wall edge is formed with a profile which blocks or at least inhibits a diffuser effect when a cooling air flow, which is guided axially through the flow passages into the annular spatial area, flows over the combustion chamber wall edge. | 05-27-2010 |
20100132369 | MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine has an engine casing component, such as a mid turbine frame system, which may includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing extend between the outer case and an inner case of the spoke casing. A bearing housing supported by the engine casing may include a fuse arrangement for isolating bearing seizure loads from the engine casing. A seal arrangement may be provided to centralize the rotors after the fuse fails. The mid turbine frame may be provided to have a desired flexibility through the configuration of the casing and bearings in design. | 06-03-2010 |
20100132370 | MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine mid turbine frame apparatus includes a an inner case supporting a bearing, an outer case to which the inner case is mounted, and an apparatus for radially positioning one relative to the other, the apparatus including a plurality of radial locators extending outwardly of the outer case and an associated locking apparatus. The locking apparatus is mounted adjacent to but independent of the locators and provides for anti-rotation of the radial locators once installed. | 06-03-2010 |
20100132371 | MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine has a mid turbine frame system which includes an outer case surrounding a spoke casing. Spokes of the spoke casing are detachably connected to the outer case and radially extend through hollow struts of a segmented interturbine duct which is disposed between the outer case and an inner case of the spoke casing. A bearing housing is supported by the inner case of the spoke casing. The mid turbine frame is assembly by inserting the interturbine duct segments over the spokes and then inserting the spoke casing into the outer case. | 06-03-2010 |
20100132372 | MID TURBINE FRAME FOR GAS TURBINE ENGINE - A gas turbine engine has a casing component, such as a mid turbine frame system, which includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing are detachably connected to the outer case and radially extend between the outer case and an inner case of the spoke casing. A bearing housing is supported by the inner case of the spoke casing. An arrangement for radially centring the bearing within the outer case is provided, the arrangement including at least three radial locators mounted to the outer case. | 06-03-2010 |
20100132373 | MID TURBINE FRAME FOR GAS TURBINE ENGINE - A mid turbine frame with an annular interturbine duct may be assembled by placing an mid turbine frame inner case of into the interturbine duct, inserting a plurality of mid turbine frame spokes radially through respective hollow radial struts of the interturbine duct to be connected to the mid turbine frame inner case to form a mid turbine frame spoke casing. A mid turbine frame outer case is also connected to the spokes, to provide an assembled mid turbine frame. | 06-03-2010 |
20100132374 | TURBINE FRAME ASSEMBLY AND METHOD FOR A GAS TURBINE ENGINE - A turbine frame assembly for a gas turbine engine includes: (a) a turbine frame including: (i) an outer ring; (ii) a hub; (ii) a plurality of struts extending between the hub and the outer ring; (b) a two-piece strut fairing surrounding each of the struts, including: (i) an inner band; (ii) an outer band; and (iii) an airfoil-shaped vane extending between the inner and outer bands; (d) a plurality of nozzle segments disposed between the outer ring and the hub, each nozzle segment being an integral metallic casting including: (i) an arcuate outer band; (ii) an arcuate inner band; and (ii) an airfoil-shaped vane. | 06-03-2010 |
20100132375 | ATTACHMENT STRUCTURE OF COMBUSTION OSCILLATION DETECTING DEVICE - In order to reduce a manufacturing cost and a running cost, casings ( | 06-03-2010 |
20100154436 | Forward sleeve retainer plate and method - In a combustor section, wherein a forward sleeve is disposed to encircle a leading end of an impingement sleeve comprised of first and second impingement sleeve parts abutted along a longitudinal junction thereof, a retainer member disposed to overlie the longitudinal junction. The retainer member is welded to at least one of said forward sleeve and the impingement sleeve. The retainer member has first and second axial end edges disposed transverse to the longitudinal junction, and at least one of the axial end edges has a cutout defined therein and disposed to overlie the longitudinal junction. | 06-24-2010 |
20100162725 | GAS TURBINE ENGINE DEVICE - A gas turbine engine adapter is provided. In one form the adapter is segmented and may be attached to a gas turbine engine support ring. The adapter can provide a channel that may receive part of a gas turbine engine component such as, but not limited to, a plug nozzle. The adapter can include a load bearing support to counteract axial forces experienced by the plug nozzle during operation of the gas turbine engine. A compressible seal can be provided between the plug nozzle and the adapter. A leaf seal can also be provided to seal between segments of the adapter. The plug nozzle can be discouraged from rotating relative to the adapter. | 07-01-2010 |
20100170267 | BURNER FOR A GAS TURBINE - A burner for a gas turbine including a main burner and a pilot burner is provided. The main burner has a supporting structure, a heat shield and a holder for the heat shield, and wherein the holder is at least partially located within the supporting structure and the heat shield is at least partially located within the holder. The heat shield is fastened to the holder by a force-fit and/or a frictional connection. | 07-08-2010 |
20100180605 | Structural Attachment System for Transition Duct Outlet - A structural attachment system for the outlet of a transition duct includes a structural attachment member that has a step over portion with an outer flange at one end thereof and an inner flange at the other end thereof. The step over portion can project away from the inner and outer flanges and can define an open area. The step over portion can have a cross-section that is generally u-shaped, v-shaped, c-shaped, semi-circular, semi-oval, parabolic, or bowed. A portion of the outlet of a transition duct is received within the step over portion of the structural attachment member. Because of such arrangement, the structural attachment member is not constrained circumferentially to fitting in between two neighboring transition ducts. The structural attachment member can manage the thermal displacements that can occur between the transitions, rotor shaft cover and first row of blades during transient engine operation. | 07-22-2010 |
20100199684 | COMBUSTION LINER ASSEMBLY SUPPORT - A combustor liner assembly support is provided that is used to axially and radially position combustor liners in a gas turbine engine. The combustor liner support includes, in one embodiment, a support bracket that is coupled to a diffuser located upstream in the gas turbine engine; a support spool coupled to the support bracket; and a mount stake coupled to the support spool. The mount stake is connected to the combustor liners and maintains the spaced relation therebetween. An alignment device can be used between the support bracket and the support spool. | 08-12-2010 |
20100218508 | System for supporting and servicing a gas turbine engine - A power system includes a gas turbine engine, which may include a gear box. The gear box may include a pipe connection configured to receive a removable pipe. The power system may also include a moveable support configured to fasten to the pipe connection to at least partially support the gear box. | 09-02-2010 |
20100229569 | Engine Exhaust System - An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct. | 09-16-2010 |
20100242493 | Fuel Nozzle Spring Support - The present application provides a fuel nozzle spring support system. The fuel nozzle spring support system may include a fuel nozzle, a cap assembly, and a spring support positioned between the fuel nozzle and the cap assembly. | 09-30-2010 |
20100242494 | CASING ARRANGEMENT - Asymmetric distortion between an inner casing and outer casing such as with regard to a gas turbine engine between an inner high pressure compressor casing and an outer combustion casing can result in problems with regard to rub between a rotary assembly within the inner casing. By providing hairpin mountings between the inner casing and outer casing such distortions can be dislocated. Individual hairpin segments are provided. These hairpin segments can be configured and formed from different material types and have different spacing distributions to tune the casing arrangement to the particular requirements and operational performance necessities of an assembly incorporating the casing arrangement. | 09-30-2010 |
20100263386 | TURBINE ENGINE HAVING A LINER - In one embodiment, a combustor of a turbine system may include a liner disposed inside the combustor. The lining element may include a heat shield having a mounting stud extending along an axis and a shell having an inner surface oriented towards the heat shield. The shell may include a passage configured to receive the mounting stud, and the mounting stud may include a structure configured to hold the heat shield apart from the inner surface of the shell along the axis of the mounting stud. | 10-21-2010 |
20100263387 | Air Filtration Sampling Point Adaptor - Air filtration sampling point adaptors for pulsed air filtration sampling of gas turbine air intakes. According to one aspect of the invention, a sampling apparatus is described. The sampling apparatus can include a mounting base plate having a first surface and a second surface, an outer tubing shell having a first end disposed on the first surface of mounting base plate, a tripod configuration coupled to the mounting base plate and the outer tubing shell and a sampling nozzle disposed on a second end of the outer tubing shell and configured to receive an air flow. | 10-21-2010 |
20100281881 | GAS TURBINE COMBUSTOR AND FUEL MANIFOLD MOUNTING ARRANGEMENT - A mounting system for locating a combustor and a fuel manifold of a gas turbine engine within a gas generator casing thereof is described. The mounting system comprises at least three support pin assemblies which extend radially inwardly from the gas generator casing. The support pin assemblies support both the fuel manifold and at least an upstream end of the combustor and maintaining engagement between the fuel manifold and the combustor during operation of the gas turbine engine. | 11-11-2010 |
20100287949 | Fastening Arrangement of a Pipe on a Circumferential Surface - A fastening arrangement of a pipe is provided. The fastening arrangement is coaxial to a longitudinal axis, on a shaft step, which is rotatably mounted around the longitudinal axis, for connecting of the two component parts, with a coaxial circumferential surface located on the shaft step, upon which circumferential surface at least partially lies the inner side of the pipe end which faces the shaft step. In order to disclose the creation of a fastening arrangement which is especially simple and inexpensive to manufacture and also free of wear during operation, it is proposed that the pipe end has notches distributed over the circumference, and an encompassing annular slot on the inner side of the pipe in the region of the notches, with a sleeve which is installed in the annular slot, covers the notches, and at least partially lies on the circumferential surface of the shaft step. | 11-18-2010 |
20100300115 | PROCESS FOR PRODUCING COMBUSTOR STRUCTURAL MEMBER, AND COMBUSTOR STRUCTURAL MEMBER, COMBUSTOR FOR GAS TURBINE AND GAS TURBINE - A process for producing a combustor structural member, the process comprising a plate-like assembly formation step of brazing a first plate-like member formed from a heat-resistant alloy, and a second plate-like member formed from a heat-resistant alloy and having a plurality of fins on the surface, with the second plate-like member positioned with the fins facing the first plate-like member, by interposing a brazing filler metal comprising a melting point lowering element between the two plate-like members, thereby forming a plate-like assembly, a press molding step of press molding the plate-like assembly to form a combustor structural member of the desired shape, a strain location identification step of identifying, in accordance with the shape of the combustor structural member, strain locations where the strain generated during the press molding step exceeds a predetermined value, a localized heating step of performing localized heating of the locations within the plate-like assembly corresponding with the strain locations identified in the strain location identification step, and a cold press molding step, which is performed as the above press molding step and comprises subjecting the plate-like assembly to cold press molding with the temperature of the heated locations corresponding with the strain locations maintained at a desired temperature. | 12-02-2010 |
20100307165 | Gas Turbine Engine Systems Involving I-Beam Struts - Gas turbine engine systems involving I-beam struts are provided. In this regard, a representative strut assembly for a gas turbine engine includes a first I-beam strut having first and second flanges spaced from each other and interconnected by a web, the first strut exhibiting a twist along a length of the web. | 12-09-2010 |
20100307166 | COMBUSTOR-TURBINE SEAL INTERFACE FOR GAS TURBINE ENGINE - A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal. | 12-09-2010 |
20110000222 | GAS TURBINE ROTOR-STATOR SUPPORT SYSTEM - A system to support a rotor and a stator of a rotating machine disposed upon a support base, the system including at least one support leg in operable communication with a bearing of the rotor and with the support base; and at least one strut in operable communication with the at least one support leg and with the stator. | 01-06-2011 |
20110000223 | GAS TURBINE COMPONENT AND A METHOD FOR PRODUCING A GAS TURBINE COMPONENT - A gas turbine component includes an inner ring, an outer ring, and a plurality of circumferentially spaced struts which are rigidly connected to the inner ring and the outer ring forming a load-carrying structure. The component includes at least one fairing connected to two adjacent struts defining a gas channel between the struts and the fairing. | 01-06-2011 |
20110005234 | CONNECTION STRUCTURE OF EXHAUST CHAMBER, SUPPORT STRUCTURE OF TURBINE, AND GAS TURBINE - In a gas turbine, an exhaust casing ( | 01-13-2011 |
20110011095 | WASHER WITH COOLING PASSAGE FOR A TURBINE ENGINE COMBUSTOR - A washer for a turbine engine combustor comprises a first surface, a second surface facing generally opposite from the first surface, a bore communicating through the first and second surfaces, and a cooling passage separate from the bore and communicating through the first and second surfaces. | 01-20-2011 |
20110016879 | LOW PROFILE ATTACHMENT HANGER SYSTEM FOR A COOLING LINER WITHIN A GAS TURBINE ENGINE SWIVEL EXHAUST DUCT - An exhaust duct assembly includes a cooling liner spaced apart from an exhaust duct case that articulate for use in a short take off vertical landing (STOVL) type of aircraft. The cooling liner assembly is attached to the exhaust duct case through a foldable attachment hanger system. The foldable attachment hanger system provides a low profile (foldable up/down) for a limited access installation envelope typical of a three bearing swivel duct (3BSD) which rotates about three bearing planes to permit transition between a cruise configuration and a hover configuration. In this way, each cooling liner segment may be formed as a complete cylindrical member requiring joints only between the swivelable duct sections. | 01-27-2011 |
20110016880 | RETAINER FOR SUSPENDED THERMAL PROTECTION ELEMENTS IN A GAS TURBINE ENGINE - A hanger system includes a pin with a head section which defines a pin axis. A clip assembly captures the head section to permit movement of the pin within a hanger in a direction traverse to the pin axis. A fastener which retains the clip assembly to the hanger. | 01-27-2011 |
20110016881 | GAS TURBINE WITH EXHAUST GAS CASING AND METHOD FOR PRODUCING A GAS TURBINE - A gas turbine ( | 01-27-2011 |
20110016882 | Electrical Cable Shroud - An electrical cable shroud forming an annular structure having an outer surface and an inner surface, the cable shroud comprising a substantially J-shaped cross-section having a longest side, a shorter leg, and a rounded portion therebetween. The longest side of the J forms the outer surface and the shorter leg forms the inner surface. The shorter leg turns inwardly and terminates in a tab extension substantially perpendicular to the outer surface, and the rounded portion forms an internal space suitable for enclosing electrical components. | 01-27-2011 |
20110016883 | Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine - The aerodynamically shaped, symmetrical cross-sectional profile for the struts or the fairing ( | 01-27-2011 |
20110030386 | MID-TURBINE FRAME - A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load shell structure and a plurality of struts. The single point load shell structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load shell structure to the mount. | 02-10-2011 |
20110030387 | MID-TURBINE FRAME TORQUE BOX HAVING A CONCAVE SURFACE - A single point load structure transfers a first load from a first bearing cone and a second load from a second bearing cone of a gas turbine engine to a plurality of struts. The single point load structure includes a stem, a branch connected to the stem and a torque box connected to the plurality of struts for absorbing the first and second loads from the stem and the branch. The stem has a concave surface that opens in a radially outward direction with respect to a rotational axis of the gas turbine engine. | 02-10-2011 |
20110061397 | CIRCUMFERENTIALLY SELF EXPANDING COMBUSTOR SUPPORT FOR A TURBINE ENGINE - A bullhorn or support for a turbine combustor is provided. The support maintains proper positioning of the transition element relative to the combustor while also allowing for certain movements of the support to alleviate mechanical stresses during turbine operation. The support is constructed from at least two pieces having an interlocking and releasable connection. | 03-17-2011 |
20110079019 | COOLING AIR SYSTEM FOR MID TURBINE FRAME - A mid turbine frame is disposed between high and low pressure turbine assemblies. A cooling air system defined in the mid turbine frame of a gas turbine engine includes internal cavities for containing pressurized cooling air to cool the inter-turbine duct and the hollow struts, and discharges the used cooling air to further cool respective high and low pressure turbine assemblies. | 04-07-2011 |
20110088407 | FUEL INJECTOR MOUNTING SYSTEM - A system is provided for mounting fuel injectors to a gas turbine engine. The system comprises an engine casing having a plurality of apertures formed therein. The system further comprises a plurality of first and second fuel injectors. Each fuel injector has a respective flange for mounting the fuel injector to the casing at a respective aperture so that the fuel injector extends into the engine. The first fuel injectors have flanges which are dismountably sealed to an inner side of the casing. The second fuel injectors have flanges which are dismountably sealed to an outer side of the casing. The flanges of the first fuel injectors are configured to allow them to pass through the apertures of the second fuel injectors. A first fuel injector can be dismounted from the casing and withdrawn therefrom through the aperture of a dismounted second fuel injector. | 04-21-2011 |
20110088408 | FUEL INJECTOR MOUNTING SYSTEM - A system for mounting a fuel injector to an engine casing with an aperture includes a fuel injector having a flange for mounting to the casing at the aperture. The flange allows it to pass through the aperture. An intermediate ring mediates the mounting of the flange to the casing at the aperture. The intermediate ring is inside the casing at the aperture and defines an opening from which the fuel injector extends into the engine with the flange positioned inward of the ring. The flange is dismountably sealed to an inner side of the ring, and the ring is dismountably sealed to an inner side of the casing to mount the fuel injector to the casing. On dismounting the flange from the ring, the fuel injector can be displaced to allow the ring, to be moved away from the aperture. The fuel injector can then be withdrawn. | 04-21-2011 |
20110088409 | FUEL INJECTOR MOUNTING SYSTEM - A combustor is provided for mounting a fuel injector to a gas turbine engine. The combustor comprises an engine casing having an aperture formed therein. The system further comprises a fuel injector having a flange for mounting the fuel injector to the casing at the aperture so that the fuel injector extends into the engine. The flange is dismountably sealed to an inner side of the casing. The aperture and flange are configured so that, when dismounted, the fuel injector can be rotated into an orientation relative to the aperture which allows the flange to pass though the aperture and the fuel injector to be withdrawn from the casing. | 04-21-2011 |
20110100019 | APPARATUS AND METHODS FOR FUEL NOZZLE FREQUENCY ADJUSTMENT - A combustion liner cap assembly includes a cylindrical outer sleeve. The cylindrical outer sleeve includes a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around the center fuel nozzle. A mounting flange assembly concentrically surrounds the cylindrical outer sleeve. A plurality of struts on an outer surface of the cylindrical outer sleeve support the mounting flange assembly. A plurality of flanges are on the outer surface of the cylindrical outer sleeve; and a plurality of support rods having first ends are adjustably supported by respective flanges. A combustor for a gas turbine includes a combustion liner cap assembly, a plurality of outer fuel nozzles supported in the plurality of outer fuel nozzle openings, and a center fuel nozzle supported in the center fuel nozzle opening. Second ends of the plurality of support rods adjustably contact the center fuel nozzle. | 05-05-2011 |
20110113789 | GAS TURBINE ENGINE COMBUSTION CHAMBER COMPRISING CMC DEFLECTORS - A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector. | 05-19-2011 |
20110120141 | COMBUSTOR SYSTEM - A combustor system is provided for a gas turbine engine. The combustor system includes an annular combustion chamber, and outer and inner casings housing the combustion chamber. The outer casing is outwardly radially spaced from the combustion chamber and the inner casing being inwardly radially spaced from the combustion chamber. The combustor system further includes an attachment arrangement at the rearward end of the combustion chamber for attaching the combustion chamber to the engine. The attachment arrangement axially restrains the rearward end of the combustion chamber relative to the casings. The combustor system further includes a first stop surface formed at the forward end of the combustion chamber adjacent a selected one of the outer and inner casings, and a corresponding first baulking surface axially forward of the first stop surface formed by the selected casing. The first stop surface and the first baulking surface are spaced from each other to allow forward axial movement of the combustion chamber relative to the selected casing. However, the amount of relative forward axial movement is limited by engagement of the first stop surface with the first baulking surface. | 05-26-2011 |
20110120142 | GAS TURBINE ENGINE FUEL CONVEYING MEMBER - A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs. | 05-26-2011 |
20110138819 | GAS TURBINE ENGINE WITH COOLING ARRANGEMENT - A gas turbine engine has an exhaust diffuser. A first path extends radially through the outer and inner cones of the diffuser and has a radially inward end and a radially outward end the inward end fluidly connected to the central cavity. An air supply or ejector is fluidly connected to the radially outward end of the first path, for drawing air by using the compressed air through the first path into the central cavity. A first opening is defined in the inner cone to fluidly connect between the exhaust channel and the central cavity. The first path and the first opening are so positioned that the cooling air is delivered from the air supply through the first path, the central cavity, and the first opening into the exhaust channel as it makes thermal contact with an object positioned in the central cavity to cool the object. | 06-16-2011 |
20110146298 | RETAINING MEMBER FOR USE WITH GAS TURBINE ENGINE SHAFT AND METHOD OF ASSEMBLY - A gas turbine engine assembly includes a rotor shaft having a threaded portion, a rotor stack support positioned radially outward from the rotor shaft, and a locking nut. The locking nut includes a body portion, a threaded portion located on a radially inner surface of the body portion, and a lug portion extending from the body portion. The rotor stack support radially rests upon the body portion of the locking nut, and the rotor stack support axially rests against the lug portion of the locking nut. The threaded portion of the locking nut and the threaded portion of the rotor shaft are engaged together. | 06-23-2011 |
20110173990 | INTERMEDIATE CASING FOR A GAS-TURBINE ENGINE - An intermediate casing for a gas-turbine engine has an outer ring ( | 07-21-2011 |
20110179804 | RADIAL TURBINE ENGINE FLOATING RING SEAL - A turbo machine is provided that includes a turbine nozzle having a wall. The wall provides spaced apart first and second surfaces. A combustor includes a liner having an annular lip that engages one of the first and second surfaces. A floating ring seal is supported by the liner in a slip-fit relationship, for example, using a retainer. The floating ring seal engages the other of the first and second surfaces. The floating ring seal is slidably moveable relative to the liner in a floating direction in response to movement of the liner in a radial direction. | 07-28-2011 |
20110179805 | ROTOR CONTAINMENT STRUCTURE FOR GAS TURBINE ENGINE - A rotor containment structure for gas turbine engine comprises an inner containment layer having a single integral body defining an annular structure about the rotor, and having a support on the inner surface of the inner containment layer for at least one shroud segment. An outer containment layer provides containment strength to contain blade fragments and defining an annular structure about the inner containment layer. Air passage through the outer containment layer for air to pass from an exterior of the outer containment layer to an interior of the outer containment layer; and the inner containment layer being connected at a first end to the outer containment layer with a gap defined between the inner surface of the outer containment layer and the outer surface of the inner containment layer, the gap being in fluid communication with the air passage such that air flows through the gap, beyond a free second end of the inner containment layer. | 07-28-2011 |
20110185746 | GAS TURBINE COMBUSTION DEVICE - The combustion device ( | 08-04-2011 |
20110192171 | TRANSITION SUPPORT SYSTEM FOR COMBUSTION TRANSITION DUCTS FOR TURBINE ENGINES - A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction. | 08-11-2011 |
20110214433 | STRAIN TOLERANT BOUND STRUCTURE FOR A GAS TURBINE ENGINE - A gas turbine engine includes bound assemblies with an inner diameter ring, struts, and an outer diameter ring. The strut is connected to the inner diameter ring and extends radially outward therefrom to connect to the outer diameter ring. A strain relief feature is disposed adjacent to or at the connection between the strut and the inner diameter ring and/or the outer diameter ring. The strain relief feature lengthens the arc segment of fillet curvature. For a constant thermal punch load, the lengthened arc segment of fillet curvature results in a decreased maximum strain in the bound assembly. | 09-08-2011 |
20110219781 | GAS TURBINE ENGINE WITH TIE SHAFT FOR AXIAL HIGH PRESSURE COMPRESSOR ROTOR - A compressor section to be mounted in a gas turbine engine has a plurality of axial compressor rotors arranged from an upstream location toward a downstream location. A tie shaft applies an axial force at one end of the compressor section and biases the compressor rotors against a hub at the opposite end. The downstream compressor is an axial compressor rotor. A gas turbine engine incorporating this structure is also claimed. | 09-15-2011 |
20110219782 | AERODYNAMICALLY SHAPED SUPPORTING AND/OR FAIRING ELEMENT IN THE BYPASS DUCT OF A GAS-TURBINE ENGINE - An aerodynamically shaped supporting and fairing element ( | 09-15-2011 |
20110219783 | TURBOJET ENGINE NACELLE WITH TRANSLATABLE UPSTREAM COWL - Turbojet engine nacelle ( | 09-15-2011 |
20110225979 | TURBO ENGINE - The invention relates to a turbo engine, in particular a gas turbine aircraft engine, having a plurality of compressor components, at least one combustion chamber and a plurality of turbine components, wherein at least one support rib ( | 09-22-2011 |
20110239661 | ROTOR FOR A GAS TURBINE ENGINE COMPRISING A ROTOR SPOOL AND A ROTOR RING - A one-piece rotor spool ( | 10-06-2011 |
20110252808 | GAS TURBINE ENGINE AND FRAME - One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique frame for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine frames. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. | 10-20-2011 |
20110265491 | COMBUSTOR CONNECTION STRUCTURE, COMBUSTOR TRANSITION PIECE, DESIGNING METHOD OF COMBUSTOR TRANSITION PIECE, AND GAS TURBINE - Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet ( | 11-03-2011 |
20110271688 | Reduced Pressure Loss Transition Support - A transition piece support for a turbomachine includes one or more support arms extending across a diffuser flowpath to the transition piece. The one or more support arms include a streamwise surface and a crosswise surface. A streamwise extent of the streamwise surface is greater than a crosswise extent of the crosswise surface to reduce flow anomalies in a flow of fluid across the one or more support arms. A turbomachine includes a combustor, a diffuser, a transition piece operably connected to the combustor and a transition piece support including one or more support arms extending across a flow of fluid to the transition piece. The support arms include a streamwise surface and a crosswise surface. A streamwise extent of the streamwise surface is greater than a crosswise extent of the crosswise surface to reduce flow anomalies in a flow of fluid across the one or more support arms. | 11-10-2011 |
20110283711 | GAS TURBINE COMPONENT AND A GAS TURBINE ENGINE COMPRISING THE COMPONENT - A gas turbine component includes an element having a relatively weak region with regard to stress loads in operation, the component including at least one elongated stiffening structure which extends on at least one side of the weak region, and the elongated stiffening structure is connected to the element in a load-transmitting manner and adapted to form a load path in its extension direction. | 11-24-2011 |
20110296847 | MOUNTING ASSEMBLY - A mounting assembly | 12-08-2011 |
20110302929 | EXHAUST GAS HOUSING FOR A GAS TURBINE AND METHOD FOR PRODUCING SAME - An exhaust gas housing for a gas turbine is provided and includes a support structure, which, arranged concentrically, includes an outer ring and an inner ring which are interconnected by radially arranged struts, and a flow liner, which is attached inside the support structure and, arranged concentrically, includes an outer liner and an inner liner which are interconnected by radially arranged liner ribs. The liner ribs each encompass the struts of the support structure, and the outer and inner liners inside the support structure form an annular passage for the turbine's hot exhaust gases. The liner ribs are welded together from front and rear parts in the flow direction, forming welded seams which extend axially in the outer liner and in the inner liner up to the liner edge. End rings, which cover the welded seams at the liner edge, are welded on the liner's rear edges for reinforcement. | 12-15-2011 |
20110308257 | ATTACHMENT STRUCTURE FOR A TURBOJET ENGINE - The present invention relates to an attachment structure ( | 12-22-2011 |
20120006037 | CLAMPING ASSEMBLY - A clamping assembly ( | 01-12-2012 |
20120017604 | GAS TURBINE ARRANGEMENT AND METHOD FOR RETROFITTING SAME - A gas turbine arrangement includes a compressor, a combustion chamber and a turbine connected to one another. A casing housing the compressor has flanges connectable to pipes providing secondary air to at least one of the combustion chamber and the turbine. The flanges define passages having an asymmetric cross section. A method for retrofitting a gas turbine arrangement is also provided. | 01-26-2012 |
20120023967 | AUXILIARY POWER UNIT WITH HOT SECTION FIRE ENCLOSURE ARRANGEMENT - A Hot Section Fire Enclosure for a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of supports mounted between a Hot Section Fire Enclosure support ring and a shroud, at least one of the supports includes a hollow support pin which spaces the Hot Section Fire Enclosure support ring relative the shroud. | 02-02-2012 |
20120023968 | EXHAUST MANIFOLD FLANGE CONNECTION - A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder. | 02-02-2012 |
20120042660 | MANIFOLD MOUNTING ARRANGEMENT - A manifold mounting arrangement comprising: a discrete manifold module; a clevis arrangement having a clevis straddling a flange and pivotally secured to the flange by a clevis pin; and a locking bar configured to be coupled to the clevis and to constrain the manifold module relative to the clevis arrangement in the locality of the locking bar. The invention finds utility for mounting case cooling manifolds to turbine casing for a gas turbine engine. | 02-23-2012 |
20120060510 | HOT GAS TEMPERATURE MEASUREMENT IN GAS TURBINE USING TUNABLE DIODE LASER - A combustion gas measurement apparatus mounted in a gas turbine including: a tunable laser generating a radiation beam passing through a combustion gas path; a controller tuning the laser to emit radiation having at least a first selected wavelength and a second selected wavelength which both correspond to temperature-dependent transitions of a combustion species of the gas, wherein the first selected wavelength and the second selected wavelength are not near absorption peaks of neighboring wavelengths; a detector sensing the radiation beam passing through the combustion gas and generating an absorption signal indicative of an absorption of the beam by the combustion gas at each of the first wavelength and the second wavelength, and a processor executing a program stored on a non-transitory storage medium determining a combustion gas temperature based on a ratio of the adoption signals for the first wavelength and the second wavelength. | 03-15-2012 |
20120073306 | GAS TURBINE COMBUSTION CHAMBER MADE OF CMC MATERIAL AND SUBDIVIDED INTO SECTORS - An assembled annular combustion chamber comprises an annular inner wall and an annular outer wall made of ceramic matrix composite material together with a chamber end wall connected to the inner and outer walls and provided with orifices for receiving injectors. Elastically-deformable link parts connect the inner wall and the outer wall of the chamber to inner and outer casings that are made of metal. The assembly formed by the inner wall, the outer wall, and the combustion chamber end wall is subdivided circumferentially into adjacent chamber sectors, each sector being made as a single piece of ceramic composite material and comprising an inner wall sector, an outer wall sector, and a chamber end wall sector. The link parts connect the inner metal casing and the outer metal casing respectively to each inner wall sector of the combustion chamber and to each outer wall sector of the chamber. The chamber end wall sectors are in contact with a one-piece ring to which they are connected. | 03-29-2012 |
20120085103 | SHIM FOR SEALING TRANSITION PIECES - According to one aspect of the invention, a shim for sealing two adjacent turbine transition pieces is disclosed. The shim includes a circumferential member that includes a first lateral flange and a second lateral flange. Further, the first and second lateral flanges each comprise a tab configured to mate to a first surface plane and the first and second lateral flanges are configured to mate to a second surface plane, wherein the first and second surface planes are substantially parallel. In addition, the shim includes a first flange extending substantially perpendicular from the circumferential member. | 04-12-2012 |
20120131928 | FLEXIBLE SEAL FOR GAS TURBINE ENGINE SYSTEM - A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections arranged about a centerline, and a connection device secured to the gas turbine engine and to the nozzle structure. The connection device is adjustable to select a length of the flexible annular seal measured along the centerline. | 05-31-2012 |
20120137705 | SHROUD SUPPORTING STRUCTURE FOR GAS TURBINE ENGINE - An annular shroud surrounding tip ends of turbine blades is fitted on an inner peripheral surface of an open end of a turbine case. In order to prevent the shroud from being dropped off in an axial direction by a retaining part provided on a retaining ring fitted on an outer peripheral surface of the open end of the turbine case, an annular groove formed in the outer peripheral surface of the turbine case and an annular groove formed in an inner peripheral surface of the retaining ring are opposed to each other, and a connection wire is inserted so as to straddle the two annular grooves, thereby connecting the retaining ring to the turbine case. Accordingly, it is possible to easily perform attachment/detachment of the retaining ring with respect to the turbine case only by inserting the connection wire into or pulling it out from the two annular grooves, thereby facilitating maintenance of the shroud and the turbine blades. Therefore, this can improve ease of attachment/detachment of the retaining ring retaining the shroud of a gas turbine engine to the turbine case. | 06-07-2012 |
20120180500 | SYSTEM FOR DAMPING VIBRATION IN A GAS TURBINE ENGINE - A system, including, a turbine combustor, including, a first wall disposed about a flow path of hot combustion gases, a second wall disposed about the first wall, and a damping system disposed between the first and second walls, wherein the damping system is configured to dampen vibration, and the damping system is tuned to dynamic drivers in the turbine combustor. | 07-19-2012 |
20120180501 | BLEED VALVE MODULE - A bleed valve module for mounting to a support structure within an aircraft includes a pipe, a plurality of bleed valves connected to the pipe, a plurality of pneumatic actuators connected to the plurality of bleed valves, and a vibration isolating element. The pipe contains a flow of bleed air and includes a plurality of inlets and an outlet. The plurality of bleed valves controls the flow of bleed air in the pipe. The plurality of pneumatic actuators actuate the plurality of bleed valves. The vibration isolating element connects the bleed valve module to the support structure within the aircraft and isolates the bleed valve module from vibration. | 07-19-2012 |
20120186269 | SUPPORT BETWEEN TRANSITION PIECE AND IMPINGEMENT SLEEVE IN COMBUSTOR - A support between a transition piece and an impingement sleeve in a combustor is disclosed. The support includes a resilient portion, the resilient portion configured to provide dampening between the transition piece and the impingement sleeve. The support further includes a mount portion configured for mounting the support to one of the transition piece or the impingement sleeve. The support further includes a contact portion configured for contacting the other of the transition piece or the impingement sleeve. | 07-26-2012 |
20120186270 | INTERSHAFT SEAL WITH SUPPORT LINKAGE - An assembly for gas turbine engine includes a cross-over housing, an inter-shaft seal housing, and a linkage. The inter-shaft seal housing is disposed within the cross-over housing. The linkage is connected to the inter-shaft seal housing and extends through a slot in the cross-over housing. The linkage is removable from both the inner radial housing and the outer radial housing. | 07-26-2012 |
20120192571 | COMBUSTOR LINER SUPPORT AND SEAL ASSEMBLY - A combination including a gas turbine engine extending along an axis is disclosed herein. The gas turbine engine includes an annular combustor having a combustor liner. The combination also includes a plurality of projections extending from the combustor liner and spaced from one another circumferentially about the axis. The combination also includes a free-standing ring disposed about the combustor liner and positioned adjacent to the plurality of projections along the axis. The plurality of projections engage the free-standing ring and circumferentially support the combustor liner while allowing relative radial displacement between the combustor liner and the free-standing ring. The combination also includes a plurality of pins each being integrally-formed with one of the plurality of projections. Each of the plurality of pins extends along the axis and is received in one of a plurality of slots formed in the free-standing ring. | 08-02-2012 |
20120198857 | CONDITION MEASUREMENT APPARATUS AND METHOD - A condition measurement apparatus is provided and includes a gas turbine engine combustor having an end cover, a liner defining a liner interior and a fuel nozzle communicative with the liner interior, the end cover being formed to separate a cold side thereof, which is a relatively low temperature environment, from a hot side thereof, which is a relatively high temperature environment in which the liner and the fuel nozzle are disposed, the combustor being formed to define a fuel flow path extending through piping disposed at the cold side of the end cover by which fuel is deliverable to the fuel nozzle, and a condition sensing device operably mounted on the piping. | 08-09-2012 |
20120204574 | GAS TURBINE ENGINE - A power turbine receiving cooling fluid from compressor apparatus is provided. The turbine comprises: fixed housing structure; a support shaft rotatably supported in the housing structure; at least one disk overhung on the support shaft and coupled to the support shaft so as to rotate with the support shaft; and cooling fluid structure. The at least one disk is formed from a low-alloy-content steel. The cooling fluid supply structure extends through the support shaft and the at least one disk so as to supply cooling fluid to the at least one disk. | 08-16-2012 |
20120204575 | FUEL INJECTOR MOUNTING SYSTEM - A system is provided for mounting fuel injectors to a gas turbine engine. The system includes an engine casing having an aperture formed therein. The system further includes a plurality of fuel injectors having respective flanges for mounting the fuel injectors to the casing at the aperture so that the fuel injectors extend side-by-side into the engine. The flanges are dismountably sealed to an inner side of the casing. The aperture and the flanges are configured so that, when dismounted, each fuel injector can be rotated into an orientation relative to the aperture which allows the respective flange to pass though the aperture and the fuel injector to be withdrawn from the casing. The flanges have respective sealing formations which engage with their neighbouring flanges when the fuel injectors are mounted to the casing to close off the aperture and to form seals between the flanges. | 08-16-2012 |
20120210729 | METHOD AND APPARATUS FOR MOUNTING TRANSITION PIECE IN COMBUSTOR - A bracket for a combustor, and a method for mounting a transition piece in a combustor, are disclosed. The combustor has an impingement sleeve at least partially surrounding a transition piece and an outer casing at least partially surrounding the impingement sleeve. The bracket is mounted to the transition piece and connected to the outer casing. The method includes mounting a bracket to the transition piece, extending the bracket through an impingement sleeve, the impingement sleeve at least partially surrounding the transition piece, and connecting the bracket to an outer casing, the outer casing at least partially surrounding the impingement sleeve. | 08-23-2012 |
20120234018 | AFT FRAME AND METHOD FOR COOLING AFT FRAME - An aft frame and a method for cooling an aft frame are disclosed. In one embodiment, an aft frame for a transition piece in a combustor is disclosed. The combustor includes the transition piece and an impingement sleeve at least partially defining a flow path therebetween. The aft frame includes a body and a generally radially extending cooling passage defined in the body, the cooling passage comprising a first end configured to accept a coolant. The aft frame further includes an exhaust passage defined in the body, the exhaust passage including a first end in communication with the cooling passage and a second end configured for communication with the flow path for flowing the coolant therethrough. | 09-20-2012 |
20120234019 | TAPERED BEARINGS - A gear support assembly for a turbine engine includes an epicyclic gear arrangement and a first tapered bearing and a second tapered bearing spaced apart from the first tapered bearing. The first tapered bearing and the second tapered bearing are arranged axially forward of the epicyclic gear arrangement and support the epicyclic gear arrangement. | 09-20-2012 |
20120240595 | COMBUSTION CHAMBER HEAD WITH HOLDING MEANS FOR SEALS ON BURNERS IN GAS TURBINES - A combustion chamber head of a gas turbine has a base plate | 09-27-2012 |
20120272660 | METHOD AND ASSEMBLY FOR RETROFITTING A GAS TURBINE COMBUSTOR END COVER - A method for retrofitting an end cover of a turbine engine combustor. The method includes inserting a first insert into a opening formed in the end cover so a circular land on the insert centers the insert in the opening and an annular face on the insert engages a face of the opening. The first insert includes a cylindrical tip section opposite the base having a diameter smaller than a diameter of the opening. The base of the first insert is joined to the opening. The method includes inserting a second insert into the opening so an outer diameter of the second insert is positioned inside the diameter of the opening. The second insert has an inner land adapted to engage the outer diameter of the first insert to position the second insert relative to the first insert and the opening. The second insert is joined to the end cover. | 11-01-2012 |
20120272661 | HEAD PART OF AN ANNULAR COMBUSTION CHAMBER - A head part of an annular combustion chamber for a gas turbine, the head part comprising: an end wall with a passage opening for accommodating a burner, the end wall comprising a back side which faces towards the combustion chamber; a burner collar adapted to fit within the passage opening and receive the burner, the burner collar comprising a protruding portion radially protruding from an outer surface of the burner collar; and a ring member for receiving the protruding portion of the burner collar; wherein the head part of the annular combustion chamber is configured such that in an installed configuration a radially outer portion of the ring member engages with the end wall and a radially inner portion of the ring member receives the protruding portion of the burner collar. | 11-01-2012 |
20120272662 | HEAD PART OF AN ANNULAR COMBUSTION CHAMBER - A head part ( | 11-01-2012 |
20120291450 | AUXILIARY POWER UNIT MOUNTING FEATURE - An auxiliary power unit assembly includes an auxiliary power unit with an auxiliary power unit exhaust duct, a bell mouth, and one or more bell mouth struts. The auxiliary power unit exhaust duct extends from the auxiliary power unit and has an aft end portion that is received within the bell mouth. The bell mouth struts extend from an inner surface of the bell mouth and extend generally radially toward the auxiliary power unit exhaust duct. | 11-22-2012 |
20120291451 | STRUCTURAL FRAME FOR GAS TURBINE COMBUSTION CAP ASSEMBLY - An intermediate support frame ( | 11-22-2012 |
20120291452 | THERMALLY COMPLIANT SUPPORT FOR A COMBUSTION SYSTEM - A support structure in a gas turbine combustor end cap ( | 11-22-2012 |
20120297790 | INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR DISK GEOMETRY FOR A GAS TURBINE ENGINE - A CMC disk for a gas turbine engine includes a CMC hub defined about an axis and a multiple of CMC airfoils integrated with the CMC hub. | 11-29-2012 |
20120297791 | CERAMIC MATRIX COMPOSITE TURBINE EXHAUST CASE FOR A GAS TURBINE ENGINE - A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone. | 11-29-2012 |
20120297792 | THERMOCOUPLE WELL FOR A TURBOMACHINE - A turbomachine includes a nozzle. The nozzle includes an end portion and an airfoil portion. A diaphragm is mounted to the end portion of the nozzle in a wheel space portion of the turbomachine. The diaphragm includes an external surface and an internal surface. The diaphragm also includes at least one thermocouple well receiving portion formed in one of the external surface and the internal surface. A thermocouple well is mounted in the at least one thermocouple well receiving portion. The thermocouple well includes a first end exposed to the wheel space portion of the turbomachine and a second end exposed at the internal surface of the diaphragm. | 11-29-2012 |
20120304664 | SYSTEM FOR MOUNTING COMBUSTOR TRANSITION PIECE TO FRAME OF GAS TURBINE ENGINE - A system includes a combustor transition piece configured to mount between a combustor and a turbine of a gas turbine engine. The combustor transition piece includes a hollow body with an internal flow passage extending from an upstream end portion to a downstream end portion. The combustor transition piece also includes an aft frame coupled to the downstream end portion of the hollow body, an aft flange coupled to the aft frame, and a mounting lug removably coupled to the aft frame at a first joint. The mounting lug is configured to removably couple to a mounting bracket at a second joint. | 12-06-2012 |
20120304665 | MOUNT DEVICE FOR TRANSITION DUCT IN TURBINE SYSTEM - A mount device and mounting assembly for a turbine system are disclosed. The mounting assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The mounting assembly further includes a mount device connecting the transition duct to the turbine section. The mount device is configured to allow movement of the outlet about at least two axes. | 12-06-2012 |
20130008176 | GAS TURBINE SHROUD ARRANGEMENT - A system for supporting a shroud used in an engine has a shroud positioned radially outboard of a rotor, which shroud has a plurality of circumferentially spaced slots; a forward support ring for supporting the shroud; the forward support ring having a plurality of spaced apart first tabs on a first side for functioning as anti-rotation devices; the forward support ring having a plurality of spaced apart second tabs on a second side; and the second tabs engaging the slots in the shroud and circumferentially supporting the shroud. | 01-10-2013 |
20130008177 | SUPPORT ASSEMBLY FOR TRANSITION DUCT IN TURBINE SYSTEM - A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes a plurality of protrusions extending from the transition duct. The plurality of protrusions are configured to allow movement of the transition duct about at least one axis. | 01-10-2013 |
20130008178 | SUPPORT ASSEMBLY FOR TRANSITION DUCT IN TURBINE SYSTEM - A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes an annular contact member extending from the transition duct. The contact member is configured to allow movement of the transition duct about at least one axis. | 01-10-2013 |
20130008179 | ULTRA HIGH TEMPERATURE CIRCUIT COUPLING - An inductance-stable ultra high temperature circuit coupling transformer ( | 01-10-2013 |
20130031913 | MOVABLE STRUT COVER FOR EXHAUST DIFFUSER - A strut cover for use in a gas turbine engine having structure defining an annular flow path for receiving exhaust gas from a turbine section of the engine. The strut cover is located downstream from a last row of blades of the turbine section and extends radially through the flow path between inner and outer walls. The strut cover includes an upstream section and a downstream section. The upstream section defines a leading edge for the strut cover and is supported on a pivot axis for pivotal movement about the pivot axis. The downstream section defines a trailing edge for the strut cover and includes an upstream end positioned adjacent to a downstream end of the upstream section. The downstream section is stationary relative to the inner and outer walls to define a predetermined flow angle for directing exhaust gases flowing from the upstream section and passing through the diffuser. | 02-07-2013 |
20130042628 | GAS TURBINE ENGINE INTERNAL COMPARTMENT STRUCTURE HAVING EGRESS FEATURE - A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure. | 02-21-2013 |
20130042629 | TURBOMACHINE LOAD MANAGEMENT ASSEMBLY - An example turbomachine load management assembly includes a support rod extending from a first rod end to a second rod end that is moveable radially relative to a fan duct, a bearing housing, or both, when the support rod is coupling the fan duct and the bearing housing. | 02-21-2013 |
20130042630 | GAS TURBINE ENGINE ACCESSORY MOUNT - A gas turbine engine accessory mount comprises a bracket fixedly attached to the engine's case, a link adapted for connection to the accessory and bracket and a fastener such as a pin disposed with a frangible fuse bushing, the pin and fuse bushing being received within aligned apertures in the link and bracket such that deflections and distortions of the engine case due to abnormal operating conditions of the engine such as a rotor imbalance due to separation of a blade therefrom, result in a shearing of the fuse busing thereby dissipating energy associated with the case deflections and distortions and isolating the fastener, link and accessory from the case deflections and distortions. | 02-21-2013 |
20130055725 | GAS DUCT FOR A GAS TURBINE AND GAS TURBINE HAVING SUCH A GAS DUCT - A gas duct for a gas turbine through which exhaust gases from the gas turbine are discharged to an outside includes a concentric inner casing and an outer casing disposed at a distance from the inner casing and concentrically encompassing the inner casing. A plurality of radial support struts interconnect the inner casing and the outer casing. Each of the support struts, the inner casing and the outer casing each have a heat-resistant lining disposed so as to provide protection against heat from the exhaust gases. The heat-resistant the linings of each of the support struts, the inner casing and the outer casing are divided in each case into a plurality of separate segments that are fastened to a support structure in an arrangement that provides an individual entirely or almost stress-free thermal expansion of each of the plurality of separate segments in an expansion plane. | 03-07-2013 |
20130067930 | AXIAL BOLTING ARRANGEMENT FOR MID TURBINE FRAME - A mid turbine frame of a gas turbine engine has a plurality of circumferentially spaced load transfer spokes extending radially between outer and inner cases. The load transfer spokes have a circumferentially enlarged inner end which is mounted to the inner case by a plurality of axially disposed fasteners extending through the inner case and spokes. | 03-21-2013 |
20130081404 | DEVICE FOR THE MUTUAL FIXATION OF TWO COMPONENTS - A device is provided for the mutual fixing of two components, which are interconnected via a flanged joint, for preventing a relative movement of the components in relation to each other in the connecting plane of the flanged joint. The device includes a key which engages in both components in a form-fitting manner in the region of the flanged joint. A simplified and flexible application is achieved by the key being guided in one of the components by means of a precision fit, whereas in the other of the components the form fit can be adjusted by adding shims. | 04-04-2013 |
20130098064 | STRUCTURAL COOLING FLUID TUBE FOR SUPPORTING A TURBINE COMPONENT AND SUPPLYING COOLING FLUID - A shaft cover support for a gas turbine engine is disclosed. The shaft cover support not only provides enhanced support to a shaft cover of the gas turbine engine, but also includes a cooling fluid chamber for passing fluids from a rotor air cooling supply conduit to an inner ring cooling manifold. As such, the shaft cover support accomplishes in a single component what was only partially accomplished in two components in conventional configurations. The shaft cover support may also provide additional stiffness and reduce interference of the flow from the compressor. In addition, the shaft cover support accommodates a transition section extending between compressor and turbine sections of the engine. The shaft cover support has a radially extending region that is offset from the inlet and outlet that enables the shaft cover support to surround the transition, thereby reducing the overall length of this section of the engine. | 04-25-2013 |
20130098065 | STRUCTURAL COOLING FLUID TUBE FOR SUPPORTING A TURBINE COMPONENT AND SUPPLYING COOLING FLUID TO TRANSITION SECTION - A shaft cover support for a gas turbine engine is disclosed. The shaft cover support not only provides enhanced support to a shaft cover of the gas turbine engine, but also includes a cooling fluid chamber for passing fluids from a rotor air cooling supply conduit to an inner ring cooling manifold. Furthermore, the shaft cover support may include a cooling shield supply extending from the cooling fluid chamber between the radially outward inlet and the radially inward outlet on the radially extending region and in fluid communication with the cooling fluid chamber for providing cooling fluids to a transition section. The shaft cover support may also provide additional stiffness and reduce interference of the flow from the compressor. In addition, the shaft cover support accommodates a transition section extending between compressor and turbine sections of the gas turbine engine. | 04-25-2013 |
20130098066 | TURBINE ENGINE COMPRISING A CONTRAROTATING PROPELLER RECEIVER SUPPORTED BY A STRUCTURAL CASING ATTACHED TO THE INTERMEDIATE HOUSING - The present invention relates to an open rotor type aircraft turbine engine ( | 04-25-2013 |
20130111924 | FLEXIBLE PRINTED CIRCUIT BOARD HARNESS - A gas turbine engine installation is provided that has a plurality of flexible printed circuit board (FPCB) harnesses to transfer electrical signals, including electrical power, around a gas turbine engine. The plurality of FPCB harnesses is held to the gas turbine engine installation using generally U-shaped clips that have a base from which first and second sidewalls extend. The FPCB harness is held between the tips of base-teeth extending from the base, and side-teeth extending from the first and second sidewalls. In this way, the FPCB harness can be held securely in position by the clip. | 05-09-2013 |
20130125559 | GAS TURBINE ENGINE COMPRISING A TENSION STUD - A gas turbine engine including a rotor is disclosed. The rotor includes a stud extending along an axis, rotating elements of a first section, and rotating elements of a second section. The stud includes a first and second external end, the first external end adapted to engage a first pre-load nut or a shaft and the second external end adapted to engage a second pre-load nut or a shaft such that the set of rotating elements are secured. Thus stud includes a first shank connected to the first external end and a second shank connected to the second external end. The first shank is located in the first section and has a first diameter. The second shank is located in the second section and has a second diameter which is greater than the first diameter. | 05-23-2013 |
20130152603 | COMBUSTION CHAMBER FOR AN AIRCRAFT ENGINE, AND METHOD FOR ATTACHING AN INJECTION SYSTEM IN A COMBUSTION CHAMBER OF AN AIRCRAFT ENGINE - A combustion chamber in which the injection system is attached so as to prevent any axial motion of the injection system, the combustion chamber includes: a baffle including a tubular portion having a first upstream end surrounded by a first radially projecting collar; and an injection system including a bowl which includes a cylindrical portion inserted into the tubular portion, the cylindrical portion including a second upstream end surrounded by a second radially projecting collar, the second collar axially bearing against the first collar, wherein the combustion chamber includes a clamp which axially clamps the first and the second collars against one another, and a fastener which retains the clamp clamped on either side of the first and second collars. | 06-20-2013 |
20130160459 | ACCESSORY MOUNTING FOR A GAS TURBINE - Accessories are mounted to a gas turbine engine from a frame attached to a pylon which is used to mount the engine to an airframe. The frame independently mounts the accessories so that engine vibrations are not transmitted to the accessories. | 06-27-2013 |
20130160460 | RIGID RAFT - The present invention provides a rigid raft formed of rigid composite material. The raft has an electrical system and/or a fluid system embedded therein. The raft further has a tank for containing liquid integrally formed therewith. The tank can be formed of the rigid composite material. The tank can be for a gas turbine engine. | 06-27-2013 |
20130160461 | ELECTRONIC UNIT MOUNTING - An electrical assembly | 06-27-2013 |
20130160462 | GAS TURBINE ENGINE PART - The present invention provides a gas turbine engine part which has a primary purpose in the engine which is structural and/or aerodynamic. The part is formed of rigid composite material, and has an electrical system comprising electrical conductors permanently embedded in the composite material. This provides advantages in terms of weight, complexity, and build time. | 06-27-2013 |
20130160463 | RAFT ASSEMBLY - A raft assembly for a gas turbine engine is provided. The raft assembly includes a rigid raft formed of a rigid material that has an electrical system and/or a fluid system embedded therein. The raft assembly further includes one or more clamps for mounting tubular members to the raft. The or each clamp has a first clamp block and a second clamp block which, in use, clamp together to grip a tubular member between the blocks. The first block is fixed to the raft. The or each clamp further has a fastener operatively extending between the blocks. The fastener is tightenable to apply a clamping load between the blocks, and releasable to remove the clamping load such that the second block can be moved relative to the first block to allow the tubular member to be received between or removed from between the blocks | 06-27-2013 |
20130160464 | ANTI-VIBRATION MOUNT - An anti-vibration mount is provided for mounting a first component to a second component. The mount has an elastomeric body which provides a recess into which the first component is received. The mount further has pair of brackets which fit to opposing sides of the elastomeric body sandwiching the first component received in the recess therebetween. At least one of the brackets is arranged to connect the anti-vibration mount and second component together. The mount further has a clamping arrangement which applies clamping pressure across the brackets and thereby compresses the elastomeric body to secure the first component in the recess. | 06-27-2013 |
20130167552 | EXHAUST STRUT AND TURBOMACHINE INCORPRATING SAME - An exhaust strut is provided and includes a body having an airfoil-shaped cross-section defining a lead edge portion and a trailing edge portion opposite the lead edge portion, the lead edge portion and the trailing edge portion being connected by a pressure side and a suction side opposite the pressure side, at least the lead edge portion and respective sections of the pressure side and the suction side proximate to the lead edge portion being formed of shape memory alloy, and a temperature control system operably disposed at the lead edge portion and the respective sections of the pressure side and the suction side proximate to the lead edge portion to modify a temperature of the shape memory alloy. | 07-04-2013 |
20130167553 | HYPERSTATIC TRUSS COMPRISING CONNECTING RODS - A hyperstatic truss including connecting rods, used for suspension of a first ring, forming part of an engine case, inside a second ring concentric to the first ring, the connecting rods being secured at one end to the first ring and at the other end to the second ring. The tensile stiffness of the connecting rods is greater than the compressive stiffness thereof. The truss for example can be used for suspension of a ducted-fan turbine engine with an elongate bypass duct. | 07-04-2013 |
20130174576 | TURBOMACHINE COMPONENT ALIGNMENT - A rotating machine has a barrel casing and at least one component carrier disposed therein. The component carrier is aligned and supported within the barrel casing using a plurality of carrier alignment fixtures which have alignment shafts that extend through the barrel casing to the component carrier. Each alignment shaft has an eccentric key pin extending from a distal end thereof and an alignment key rotatably-mounted to each eccentric key pin. The alignment keys mate with corresponding keyway slots defined on the component carrier such that when the carrier alignment fixtures are rotated axially, the corresponding alignment keys bias against the keyway slot and shift the position of the component carrier. | 07-11-2013 |
20130186103 | NEAR FLOW PATH SEAL FOR A TURBOMACHINE - A near flow path seal for a turbomachine includes a support member having a first end portion that extends to a second end portion through an intermediate portion, and an arm member extending from the first end portion of the support member. The arm member includes a first end that extends to a second end, a first surface extending between the first and second ends, and a second, opposing surface extending between the first and second ends. The second surface includes a plurality of surface features that extend from about the first end toward the second end. | 07-25-2013 |
20130186104 | ARRANGEMENT OF COMPONENTS OF A WIND POWER PLANT - An arrangement of components ( | 07-25-2013 |
20130192255 | FIXTURE ASSEMBLY FOR REPAIRING A SHROUD TILE OF A GAS TURBINE - A fixture assembly for securing at least one side rail to a shroud tile of a gas turbine is disclosed. The fixture assembly may include a first support member, a second support member, a first guide block and a second guide block. The first and second guide blocks may be formed from a material that has the same or a similar coefficient of thermal expansion as the material used to form at least one of the shroud tile and the at least one side rail. In addition, the first and second support members may be formed from a material that has a lower coefficient of thermal expansion than the material used to form the first and second guide blocks. | 08-01-2013 |
20130192256 | GEARED TURBOFAN ENGINE WITH COUNTER-ROTATING SHAFTS - A mid-turbine frame is incorporated into a turbine section of a gas turbine engine intermediate a high pressure turbine and a low pressure turbine. The high pressure and low pressure turbines rotate in opposite directions. The mid-turbine frame carries a plurality of vanes to redirect the flow downstream of the high pressure turbine as it approaches the low pressure turbine. In another feature, a power density is defined as the thrust divided by the volume of a turbine section, and the power density is of about 1.5 lbf per in | 08-01-2013 |
20130192257 | TURBINE SHROUD HANGER WITH DEBRIS FILTER - A turbine shroud hanger apparatus for a gas turbine engine includes: an arcuate shroud hanger having at least one cooling hole passing therethrough, the cooling hole having an inlet and an outlet; and a filter carried by the shroud hanger positioned upstream of the inlet of the cooling hole, the filter having a plurality of openings formed therethrough which are sized to permit air flow through the cooling hole while preventing the entry of debris particles larger than a preselected size into the cooling hole. | 08-01-2013 |
20130213056 | DAMPING DEVICE FOR DAMPING PRESSURE OSCILLATIONS WITHIN A COMBUSTION CHAMBER OF A TURBINE - A damping device for damping pressure oscillations within a combustion chamber of a turbine is provided. The damping device has a radially extending damping device body. The damping device body has a radially inner circumferential edge portion and a radially outer circumferential edge portion. A through hole is formed in the damping device body and has a tapered shape. | 08-22-2013 |
20130227962 | DEVICE FOR CONNECTING A THRUST REVERSER FRONT FRAME TO A FAN CASING AND NACELLE INCORPORATING SUCH A DEVICE - A device for connecting a thrust reverser front frame to a fan casing includes a crenulated flange secured to the front frame, an annular component to accept this flange secured to the fan casing, and a crenulated annulus of a shape that complements the flange and pivot-mounted on the annular component. The crenulated flange, the annular component and the crenulated annulus are designed in such a way that a rotation of the annulus with respect to the annular component has the effect of locking this flange against this annular component through the collaboration between the respective crenulations of the flange and of the annulus. | 09-05-2013 |
20130255276 | Transition Duct Mounting System - The present invention is directed to a mounting system for a gas turbine transition duct. The mounting system includes a generally C-shaped mounting bracket having a generally radially extending first portion, an arc-shaped second portion, and a generally radially extending third portion. Each of the first portion and third portion includes a spherical bearing and the second portion has a plurality of sets of mounting holes. In another embodiment of the present invention, a gas turbine transition duct is provided having a panel assembly, an aft frame secured to the panel assembly and a mounting system for securing the transition duct to a turbine inlet. The panel assembly includes two formed sheets of metal secured together along axial seams. The panel assembly is secured to an aft frame that is capable of expanding in the circumferential direction due to thermal growth. The mounting system comprises a generally C-shaped mounting bracket having a generally radially extending first portion, an arc-shaped second portion, and a generally radially extending third portion. Each of the first portion and third portion includes a spherical bearing and the second portion has a plurality of sets of mounting holes. | 10-03-2013 |
20130319000 | TURBINE GEAR ASSEMBLY SUPPORT HAVING SYMMETRICAL REMOVAL FEATURES - An exemplary gear assembly support for use in a gas turbine engine includes a support member having a portion that is configured to be coupled to a gear assembly. Another portion of the support member is configured to be coupled to a housing in a gas turbine engine. The support member includes a plurality of removal features that each have a plurality of engaging surfaces to facilitate a pulling force on the support member in a direction parallel to an axis through a center of the support member. The engaging surfaces on each of the removal features are oriented relative to each other to resist any bending moment on the support member during application of the pulling force. | 12-05-2013 |
20130319001 | TURBINE GEAR ASSEMBLY SUPPORT HAVING SYMMETRICAL REMOVAL FEATURES - An exemplary gear assembly support for use in a gas turbine engine includes a support member having a portion that is configured to be coupled to a gear assembly. Another portion of the support member is configured to be coupled to a housing in a gas turbine engine. The support member includes a plurality of removal features that each have a plurality of engaging surfaces to facilitate a pulling force on the support member in a direction parallel to an axis through a center of the support member. The engaging surfaces on each of the removal features are oriented relative to each other to resist any bending moment on the support member during application of the pulling force. | 12-05-2013 |
20140013768 | MULTIPURPOSE SUPPORT SYSTEM FOR A GAS TURBINE - A system includes a gas turbine engine and a multipurpose gas turbine engine support frame couple to the gas turbine engine. The multipurpose gas turbine support frame is configured to support the gas turbine engine during both operation and transport of the gas turbine engine. | 01-16-2014 |
20140013769 | MID-TURBINE FRAME WITH OIL SYSTEM MOUNTS - A gas turbine engine includes a combustor, a first turbine section in fluid communication with the combustor, a second turbine section in fluid communication with the first turbine section, and a mid-turbine frame located axially between the first turbine section and the second turbine section. An oil system includes a first oil system component that houses oil. A first connector mechanically connects the first oil system component to the mid-turbine frame. | 01-16-2014 |
20140013770 | VANE INSERTABLE TIE RODS WITH KEYED CONNECTIONS - A gas turbine engine includes a combustor, a first turbine section in fluid communication with the combustor, a second turbine section in fluid communication with the first turbine section, and a mid-turbine frame located axially between the first turbine section and the second turbine section. The mid-turbine frame includes a first frame case, a second frame case, a vane positioned between the first frame case and the second frame case, and a spoke extending through the vane and connecting the first frame case to the second frame case. The spoke includes a tie rod having a first end connected to the first frame case at a keyed connection. | 01-16-2014 |
20140026590 | FLEXIBLE COMBUSTOR BRACKET - A bracket for an augmentor assembly of a gas turbine engine includes a first mount attachable to a support structure. A second mount is attachable to an augmentor pilot assembly and extends radially inward of the support structure. First and second spring members attach on a first end to the first mount and on a second end to the second mount. The first and second spring members include a center spring portion spaced apart from one another to allow sufficient relative radial and circumferential movement to accommodate differential thermal expansions throughout operation of the augmentor. | 01-30-2014 |
20140026591 | AXIAL RETENTION FOR FASTENERS IN FAN JOINT - In a gas turbine engine, a fan rotor and a compressor rotor are connected to a joint which is attached to a shaft. The fan rotor is connected to the joint by a plurality of fasteners extending through mounting openings in the joint and through apertures in the fan rotor. A standard retaining ring is attached to the joint to cover a portion of an enlarged head of each of the respective fasteners in order to prevent removal of the respective fasteners from the mounting openings in the joint before the respective fasteners are connected to the fan rotor. | 01-30-2014 |
20140026592 | ASSEMBLY FOR A JET ENGINE OF AN AIRCRAFT - The present invention proposes a structural unit for an aircraft engine having at least one fuel pump of a fuel circuit and at least one hydraulic fluid pump of a hydraulic fluid circuit, where the structural unit can be coupled to an accessory gearbox shaft of an accessory gearbox of the engine. | 01-30-2014 |
20140033734 | STATOR ANTI-ROTATION LUG - A compressor assembly of a gas turbine engine includes a case including at least one opening and a stator assembly supported within the case. A lug assembly is secured to the case and sets a position of the stator assembly relative to the case. The lug assembly includes a lug engaging the stator assembly and a boss extending from the lug through the opening in the case. The boss including a threaded hole receiving a threaded member holding the lug assembly to the case and defines a seat for the threaded member that is spaced apart from an outer surface of the case. | 02-06-2014 |
20140047848 | ADJUSTABLE CABLE FOR EXHAUST DUCT LINER HANGER - A hanger for suspending a liner within an exhaust duct of a gas turbine engine exhaust system comprises a connector assembly, a cable and a bracket. The connector assembly is for connecting to an exhaust duct of the gas turbine exhaust system. The cable extends from the connector assembly and is configured to extend into the exhaust duct. The bracket is for connecting to an exhaust duct liner of the gas turbine exhaust system. The bracket is connected to the cable. | 02-20-2014 |
20140047849 | SPHERICAL BUTTON WASHER FOR EXHAUST DUCT LINER HANGER - A hanger for suspending a liner within an exhaust duct of a gas turbine engine comprises a bracket, a washer, a rod and a cap. The bracket is for connection to an exhaust duct liner of a gas turbine exhaust system. The washer is connected to the bracket at a slip joint. The rod is connected to the washer at a ball joint. The cap for is for connecting to an exhaust duct of the gas turbine exhaust system. The cap is connected to the rod. | 02-20-2014 |
20140053573 | HOT GAS EXPANDER INLET CASING ASSEMBLY AND METHOD - A gas turbine device includes an inlet casing and a stator diaphragm provided inside the inlet casing. The stator diaphragm has an integral inner stator shroud and an outer stator shroud and a plurality of stator vanes provided in a circumferential arrangement between the inner stator shroud and the outer stator shroud. A plurality of key slots is provided in a circumferential arrangement on the stator diaphragm and a corresponding plurality of key slots is provided in a circumferential arrangement on the inlet casing. The key slots provided on the stator diaphragm are aligned with the plurality of key slots provided on the inlet casing. A key is inserted into each of the plurality of key slots provided to prevent rotation of the stator diaphragm with respect to the inlet casing. The stator diaphragm is secured in an axial direction by a stator shear ring. | 02-27-2014 |
20140060077 | COMBUSTOR - A combustor includes a breech end, a fuel nozzle connected to the breech end and extending downstream from the breech end, and a shroud that circumferentially surrounds the fuel nozzle inside the combustor. A support extends radially inside at least a portion of the shroud, and a flexible coupling is between the support and the fuel nozzle. An adjustable tensioner is configured to engage with the flexible coupling and constrain longitudinal extension of the flexible coupling. | 03-06-2014 |
20140060078 | COMBUSTOR - A combustor includes a breech end, a plurality of fuel nozzles connected to the breech end and extending downstream from the breech end, and a shroud that circumferentially surrounds the plurality of fuel nozzles inside the combustor. A support extends radially inside at least a portion of the shroud. A leaf spring is between the support and one or more of the plurality of fuel nozzles, wherein each leaf spring includes at least three leaves. | 03-06-2014 |
20140069106 | SLIDING U-JOINT HANGER FOR GAS TURBINE ENGINE NOZZLE - A disclosed hanger assembly for supporting a liner within a gas turbine engine exhaust nozzle includes a first mount for attachment to a case and a second mount for attachment to the liner. A u-joint assembly is attached between the first and second mounts and includes a first yoke and a second yoke aligned transverse to the first yoke. A pivot block is includes a first set of pins received by the first yoke and a second set of pins received by the second yoke. The u-joint assembly accommodates relative movement between the liner and case. | 03-13-2014 |
20140090398 | FLEXIBLE CONNECTION BETWEEN A WALL AND A CASE OF A TURBINE ENGINE - A wall assembly includes a wall that extends axially along a centerline, and circumferentially at least partially around the centerline. The wall assembly also includes a plurality of mounting brackets arranged circumferentially around the centerline, and a plurality of wall brackets. Each of the mounting brackets includes a groove that extends axially into the respective mounting bracket. Each of the wall brackets includes a tongue and a base. The tongue extends axially from the base into the groove of a respective one of the mounting brackets. The base is connected to the wall. | 04-03-2014 |
20140090399 | PANEL SUPPORT HANGER FOR A TURBINE ENGINE - A support hanger is provided for a turbine engine. The support hanger includes a pin with a pin head, a retainer and a flexible seal. The retainer is pivotally connected to the pin head. The retainer includes a seal bearing surface facing towards the pin head. The seal includes a retainer bearing surface sealingly engaging the seal bearing surface. | 04-03-2014 |
20140090400 | VARIABLE FLOW DIVIDER MECHANISM FOR A MULTI-STAGE COMBUSTOR - The present invention discloses a novel apparatus and way for altering the airflow to a gas turbine combustion system. The apparatus comprises a flow divider mechanism which splits the airflow surrounding a combustion liner into two distinct portions, one directed towards a pilot and one directed towards a main stage combustion. The flow divider mechanism is interchangeable so as to provide a way of altering airflow splits between stages of the combustion system. | 04-03-2014 |
20140096537 | Thin Metal Duct Damper - A damper for damping vibration of a structural member of a gas turbine engine is disclosed. The damper may include a first metal mesh pad which abuts an outer circumferential surface of the structural member, and a garter spring which abuts the first metal mesh pad. Both the metal mesh pad and the garter spring may completely or partially encircle the structural member. Alternatively, the damper may include a damper cover which encloses the first metal mesh pad and the garter spring and which abuts the outer surface of the structural member. A second metal mesh pad may be inserted between the damper cover and the garter spring. A gas turbine engine which comprises such a damper is also disclosed. | 04-10-2014 |
20140109592 | LEAF SPRING HANGER FOR EXHAUST DUCT LINER - A hanger assembly for use between a first duct and a second duct has a flexible leaf spring having a body and a leg, a locking member for attaching the leg to the first duct, and a mounting member for attaching the body to the second duct. | 04-24-2014 |
20140109593 | COIL SPRING HANGER FOR EXHAUST DUCT LINER - A hanger assembly for use between a first duct and a second duct having an opening therein includes a spring having a first end and a second end, a first mount for attaching the first end to the first duct, a second mount for attaching the second end to the second duct, the second mount having an area greater than the opening, and a central aperture therethrough. | 04-24-2014 |
20140109594 | Deformable Mounting Assembly - A deformable fastener assembly for use with a gas turbine engine. The deformable fastener may be used to fasten a component of the gas turbine that is subjected to high temperatures and thermal deformation, such as an impingement sleeve assembly, to a rigid portion, such as the inner turbine shell of the gas turbine engine. The deformable fastener assemblies may permit components to be fastened to a rigid portion of the gas turbine with a consistent load input to permit frictional transient sliding of the component relative to the rigid portion of the gas turbine engine. | 04-24-2014 |
20140109595 | ANNULAR COMBUSTION CHAMBER OF A TURBOMACHINE - An annular combustion chamber for a turbomachine presenting an axial direction, a radial direction, and an azimuth direction, the combustion chamber including a first annular wall and a second annular wall, each annular wall defining at least a portion of an enclosure of the combustion chamber. The first annular wall and the second annular wall present complementary assembly mechanisms that co-operate by engagement in azimuth. | 04-24-2014 |
20140109596 | ARRANGEMENT FOR CONNECTING A DUCT TO AN AIR-DISTRIBUTION CASING - An arrangement for connecting at least one duct with an air-distribution casing, the at least one duct including two sidewalls opposite one another and including a peripheral wall connecting edges of the two sidewalls. The arrangement includes a connecting tube that extends through the casing, passes through an orifice associated with each of the two sidewalls, and is connected to the at least one duct. A system controlling clearance of a turbo engine and a turbo engine can include air-injection ducts connected to the distribution casing by such an arrangement. | 04-24-2014 |
20140123677 | GAS TURBINE ENGINE AIRFOIL PROFILE - An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body including a leading edge and a trailing edge joined by a pressure side and a suction side spaced apart from the pressure side to provide an external airfoil surface extending in a radial direction from at least one platform. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to ±0.050 inches (±1.27 mm). | 05-08-2014 |
20140130511 | COMBUSTOR CONNECTION STRUCTURE, COMBUSTOR TRANSITION PIECE, DESIGINING METHOD OF COMBUSTOR TRANSITION PIECE AND GAS TURBINE - A cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79£DoutDin£0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out. | 05-15-2014 |
20140137567 | MICRO GAS TURBINE HAVING IGNITOR-COUPLING STRUCTURER AND METHOD OF ASSEMBLING THE SAME - Disclosed are a micro gas turbine and a method of assembling the same. The micro gas turbine includes an ignitor assembly having an ignitor, along with an ignitor-coupling structure. The ignitor-coupling structure includes a mounting bracket having first and second ends, the first end being coupled to the ignitor and the second end being provided on its outer circumference with an external screw. A coupling member is mounted to a liner casing surrounding a combustor and has, on its inner circumference, an internal screw corresponding to the external screw. A bellows surrounds the mounting bracket. | 05-22-2014 |
20140137568 | DEVICE FOR MOUNTING A SPARK PLUG IN A COMBUSTION ENGINE OF A GAS TURBINE ENGINE - A device for mounting a spark plug in a combustion chamber of a gas turbine engine includes a chimney including a collar extending radially inwards, a washer fastened on an axial end of the chimney so as to project towards the inside of the chimney, and a bushing forming a spark plug guide and including an inner collar and an outer collar that are axially spaced apart from each other by a cylindrical portion. Each collar extends radially outwards. The bushing is floatingly mounted inside the chimney with its collars axially positioned between the collar of the chimney and the washer. The inner collar comes in operation to bear against the collar of the chimney. The outer collar presents an outside diameter (d1) greater than the inside diameter (d2) of the washer. | 05-22-2014 |
20140150450 | EXHAUST COMPONENT MOUNTING STRUCTURE - An exhaust after-treatment system including a first exhaust treatment device having a first mounting surface and a second mounting surface, and a second exhaust treatment device and a third mounting surface and a fourth mounting surface. A first mounting structure is attached to the first mounting surface of the first exhaust treatment device, and a second mounting structure attached to the third mounting surface of the second exhaust treatment device, wherein the second and fourth mounting surfaces are secured to each other. | 06-05-2014 |
20140150451 | BAND STRUCTURE AND MICRO GAS TURBINE HAVING THE SAME - Disclosed are a band structure and a micro gas turbine having the same. An insert wall and a nozzle ring casing are respectively surrounded in part by a first band structure of a heat resistant material and a second band structure of a material that is identical or similar to the material of the first band structure to prevent thermal deformation of the insert wall and of the nozzle ring casing and a nozzle vane so as to maintain constant gaps between a blade tip of a turbine wheel and the insert wall and between a leading edge of the turbine wheel and the nozzle vane, thereby preventing reduction in both the power output of the turbine wheel even after a prolonged drive period and the operation efficiency of the micro gas turbine. | 06-05-2014 |
20140150452 | TRANSITION PIECE FOR A GAS TURBINE SYSTEM - A system includes a gas turbine transition piece. The gas turbine transition piece includes a duct body having a forward end portion and an aft end portion. The duct body defines an enclosure for routing a flow of combustion products from a combustor to a turbine first stage nozzle, and the forward end portion includes a straight portion extending in a downstream direction of the flow. The gas turbine transition piece also includes a first set of dilution holes formed in the forward end portion and arranged in a first pattern configured to reduce emissions. In certain embodiments, the gas turbine transition piece includes a second set of dilution holes formed in the aft end portion and arranged in a second pattern configured to alter the thermal gradient of the combustion gases. | 06-05-2014 |
20140150453 | Gas Turbine Combustion Chamber - A gas turbine combustion chamber is provided, including a flow sleeve structure with an improved anti-vibration performance. A gas turbine combustion chamber of the present invention includes a liner, a transition piece, and a flow sleeve including a plurality of segments and integrated by welding a tie piece along joint portions of the segments. The tie piece includes a first member and a second member, the first member continuously extending along a longitudinal direction of the joint portions of the segments and being arranged to cover the joint portions, and the second member being formed at an end portion of the first member, having a width wider than the first member, and including a recess. | 06-05-2014 |
20140182308 | GAS TURBINE ENGINE WITH V-BAND CLAMP CONNECTION FOR COLLECTOR BOX - A gas turbine engine includes a turbine section, a compressor section, a bleed air collector box, and a v-band clamp. The compressor section is positioned upstream of the turbine section and includes a compressor case circumferentially surrounding the compressor section. The v-band clamp attaches the bleed air collector box to the compressor case. | 07-03-2014 |
20140196471 | FAN DRIVE GEAR SYSTEM FLEXIBLE SUPPORT FEATURES - A disclosed gear assembly support for a gas turbine engine includes a first portion configured for attachment to a case of the gas turbine engine and a second portion configured for supporting a gear assembly. The support further includes a snap portion defining a fit within the case. The snap portion includes a tunable feature for adjusting a fit within the case. A torque reacting portion of the support transfers torque from the second portion to the first portion separate from the snap portion and include separately tunable features fore adjusting the snap fit independent of the torque transfer portions. | 07-17-2014 |
20140202168 | CONTINUOUS RING COMPOSITE TURBINE SHROUD - A composite annular shroud supported by a support assembly including at least one ring and at least partially disposed within the ring. The shroud is biased against and in sealing engagement with an inner flange of the ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring. | 07-24-2014 |
20140216054 | Variable Volume Combustor with Aerodynamic Support Struts - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and providing the flow of fuel therethrough. The support struts may include an aerodynamic contoured shape so as to distribute evenly a flow of air to the micro-mixer fuel nozzles. | 08-07-2014 |
20140216055 | GAS TURBINE - In this gas turbine, at a downstream portion of a transition piece of a combustor, inner surfaces of a pair of lateral walls facing each other in a circumferential direction of a turbine rotor form inclination surfaces that incline down to a downstream end of the transition piece in a direction approaching the transition piece of another adjacent combustor that gradually draws closer as it goes to the downstream side of the transition piece in an axis direction. | 08-07-2014 |
20140245750 | CIRCUMFERENTIALLY RETAINED FAIRING - An assembly for a gas turbine engine includes a frame, a mount, and a fairing. The mount is attached to the frame and the fairing is connected to the mount. The fairing and mount have mating anti-deflection features that engage to prevent circumferential movement of the fairing relative to the frame. | 09-04-2014 |
20140245751 | PASSAGES TO FACILITATE A SECONDARY FLOW BETWEEN COMPONENTS - An annular mount for a gas turbine engine includes a first flange and a second flange. The first flange has an arcuate shape, and the second flange extends from the first flange. The second flange has an interface surface along at least one side and has a plurality of mounting apertures extending therethrough. The channels extend along a length of the interface surface from a first edge to a second edge. | 09-04-2014 |
20140250915 | CENTERLINE SUPPORT BAR FOR STEAM TURBINE COMPONENT - A centerline support bar for steam turbine component assembly, installation, and/or alignment is disclosed. In one embodiment, the support bar includes a body portion configured to be disposed across a centerline of a steam turbine, the body portion configured to transversely connect to a steam turbine component; and a first flange extending from the body portion and configured to contact a steam turbine casing, wherein the steam turbine support bar is configured to non-affixedly join the steam turbine casing to the steam turbine component. | 09-11-2014 |
20140260315 | SYSTEM HAVING MULTI-TUBE FUEL NOZZLE WITH FLOATING ARRANGEMENT OF MIXING TUBES - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes an end cover, a first plate, and multiple tubes. The multiple tubes are disposed and supported in a floating arrangement between the end cover and the first plate. Each tube includes a forward end adjacent the end cover and an aft end adjacent the first plate. | 09-18-2014 |
20140260316 | GAS TURBINE TRANSITION INLET RING ADAPTER - A combustion system for a gas turbine engine including a combustor assembly comprising a combustor basket having a downstream terminal end, and a transition duct extending downstream from the combustor basket and having an upstream end located adjacent to the downstream terminal end of the combustor basket. A coupling is provided comprising an inlet ring adapter including a cylindrical sleeve extending downstream of the upstream end of the transition duct in overlapping relation to an inner surface of the transition duct. A spring clip assembly is mounted to the terminal end of the combustor basket. The spring clip assembly extends into engagement with and forms a seal on the cylindrical sleeve. | 09-18-2014 |
20140260317 | GAS TURBINE COMBUSTOR EXIT PIECE WITH HINGED CONNECTIONS - An exit piece ( | 09-18-2014 |
20140260318 | SIDE SEAL SLOT FOR A COMBUSTION LINER - A side seal slot extends along a one side of an aft frame for a combustion liner of a gas turbine. The side seal slot is at least partially defined between a downstream wall and an upstream wall that extend outward from the first side of the aft frame. A first segment of the upstream wall extends from an inner portion of the aft frame towards an outer portion of the aft frame at a first outward distance from the first side. A second segment of the upstream wall extends from the first segment to the outer portion of the aft frame at a second outward distance from the first side. The second segment of the upstream wall at least partially defines a side seal guide feature to allow for axial insertion of a bottom portion of a side seal into the side seal slot. | 09-18-2014 |
20140260319 | COMBUSTOR SUPPORT ASSEMBLY FOR MOUNTING A COMBUSTION MODULE OF A GAS TURBINE - A gas turbine comprises a compressor discharge casing that is coupled to an outer turbine shell. The compressor discharge casing includes a combustor opening that extends through the compressor discharge casing and an outer mating surface that circumferentially surrounds the combustor opening. The outer turbine shell defines an inner mating surface. A combustion module extends through the combustor opening. The combustion module includes a forward end that is circumferentially surrounded by a mounting flange and an aft end that is circumferentially surrounded by an aft frame. The mounting flange extends circumferentially around the combustor opening. The mounting flange is coupled to the outer mating surface of the compressor discharge casing and the aft frame is coupled to the inner mating surface of the outer turbine shell. | 09-18-2014 |
20140260320 | BI-METAL FASTENER FOR THERMAL GROWTH COMPENSATION - An improved fastening system and method overcomes traditional thermal mismatch that occurs with standard fastener systems that are employed in extreme temperature environments. The fastening system could employ a metallic fastener that is combined with metallic spacer, each of which having a differing thermal growth coefficient. This arrangement may reduce thermal expansion by several orders of magnitude over the range of temperatures where the thermal fastener can be applied. Such an improved fastening system may be employed in gas turbine machines and in other locations where it is desirable to improve fastening of objects in extreme temperature environments. | 09-18-2014 |
20140260321 | GAS TURBINE ENGINE STATIC STRUCTURE JOINT WITH UNDERCUTS - A gas turbine engine static structure has a joint that includes at least two flanges. The first flange includes a face extending axially proud between radially spaced apart undercuts. The second flange abuts the face. Fasteners secure the flanges to one another through the face. | 09-18-2014 |
20140283528 | Aftertreatment Module and Method of Assembly - To assemble an aftertreatment module for use in the treatment of exhaust gasses and the like, an aftertreatment brick is inserted into a sleeve opening in a sleeve and advanced toward an opposite end of the sleeve. To retain the aftertreatment brick in the sleeve, the end of the sleeve can include a stop flange and the aftertreatment brick can include a mantle flange. The stop flange and the mantle flange can abut against each other to prevent further movement of the aftertreatment brick through the sleeve. To seal against exhaust gasses leaking though the module, a gasket can be disposed between the stop flange and the mantle flange. Exterior ribs disposed around the aftertreatment brick can assist concentric alignment between the flanges and gasket. | 09-25-2014 |
20140290268 | GAS TURBINE ENGINE GEARED ARCHITECTURE AXIAL RETENTION ARRANGEMENT - A gas turbine engine includes a fan, an engine static structure, a geared architecture to drive the fan and supported relative to the static structure, a fan drive turbine to drive the geared architecture, a first member secured to the geared architecture, and a second member secured to the engine static structure and configured to cooperate with the first member to limit movement of the geared architecture relative to the static structure. A fan drive gear system and method are also disclosed. | 10-02-2014 |
20140305134 | RIGID RAFT FOR A GAS TURBINE ENGINE - A rigid raft is provided for a gas turbine engine. The raft has an electrical system and/or a fluid system embedded in the material of the raft. The raft further has one or more first mounts for mounting the raft to the gas turbine engine, and one or more second mounts for mounting a gas turbine engine component to the raft. The raft further has one or more tethers which extend between respective first and second mounts and are embedded in the material of the raft. | 10-16-2014 |
20140311160 | HYBRID TURBOMACHINE ENCLOSURE - A hybrid turbomachine enclosure includes a plurality of walls interconnected to form an interior configured and disposed to receive a turbomachine, the plurality of walls including a first wall having a panel on frame construction and a hybrid wall including a first portion having a panel on frame structure and a second portion having a stiffened frame panel structure. | 10-23-2014 |
20140311161 | METHOD FOR CREATING A CONNECTING ELEMENT POSITIONED BETWEEN TWO COMPONENTS OF A STRUCTURE, CONNECTING ELEMENT AND BYPASS TURBOJET ENGINE COMPRISING SUCH A CONNECTING ELEMENT - A method for creating a connecting element, arranged between two components of a structure, or a turbojet engine structure, which is subjected to compressive and/or tensile loadings and which includes a hollow shaft immersed, at least partially, in a stream of air flowing between the two components, the method including: dimensioning a width of the main cross section associated with the shaft of the connecting element in a direction orthogonal to the longitudinal axis of the shaft according to desired mechanical strength and desired mass, and according to characteristics of the airstream; and working an external surface of the shaft of the connecting element, at least over part of this surface, to give it a surface finish with an arithmetic mean roughness at least equal to 20 microns, to reduce drag of the connecting element thus dimensioned by comparison with a smooth connecting element of the same diameter. | 10-23-2014 |
20140318148 | BURNER SEAL FOR GAS-TURBINE COMBUSTION CHAMBER HEAD AND HEAT SHIELD - The present invention relates to a combustion chamber for a gas turbine with a combustion chamber head and a heat shield which are designed in one piece, with the heat shield being provided with at least one recess, in which is arranged a burner or an annular sleeve enclosing the burner, with a burner seal being provided between the heat shield and the burner, characterized in that the heat shield is provided in the area of the recess with an annular groove, in which is arranged at least one elastic sealing element forming the burner seal. | 10-30-2014 |
20140318149 | SEAL FOR A TURBOJET ENGINE PYLON AND NACELLE, AND TURBOJET ENGINE PYLON-NACELLE ASSEMBLY INCORPORATING SUCH A SEAL - A fire-resistant seal for a propulsion assembly which includes a pylon, an O-duct type nacelle of a turbojet engine. The nacelle includes an inner fixed nacelle structure and a combustion gas ejection primary nozzle, and the fire-resistant seal is placed in an annular sector defined by the inner fixed nacelle and the gas ejection primary nozzle. In particular, the fire-resistant seal includes a plurality of baffles, and the plurality of baffles are longitudinally disposed so as not to interfere each other during a longitudinal translational movement of the inner fixed nacelle structure relative to the combustion gas ejection primary nozzle. | 10-30-2014 |
20140325992 | ELECTRICAL UNIT WITH ELECTRICAL CONNECTOR - An electrical unit comprises an electrical connector having a set of elongate electrical terminals which are each a one-piece component. The terminals extend into the unit such that first ends of the terminals are connected to multiple electrical conductors within the unit and second ends of the terminals project from a surface of the unit. A collar is formed at the surface of the unit to at least partially encircle the projecting second ends. This arrangement allows the unit to be electrically connected at the electrical connector by press fitting to a terminating region of a flexible electrical harness, the collar defining a recess in which the terminating region is located. | 11-06-2014 |
20140325993 | ELECTRICAL HARNESS CONNECTOR - An electrical harness assembly is provided that comprises a flexible printed circuit electrically connected to one end of an electrical connector. The other end of the electrical connector is presented for connection to another electrical component. Electrical tracks or conductors in the flexible printed circuit terminate in receiving holes. The electrical connector comprises terminals, each of which has a first end that is received in one of the receiving holes to form a connection formation, and a second end which is present for connection to the other electrical device. The connection formation is encapsulated so as to be sealed, thereby providing a reliable and robust connection between the connector and the flexible printed circuit. | 11-06-2014 |
20140366555 | ACCESSORY MOUNTING FOR A GAS TURBINE ENGINE - A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. The frame is attached to the pylon at forward and rearward engine mounting locations. The frame comprises at least one hollow tube and at least one duct is arranged to supply coolant into the at least one hollow tube and the at least one hollow tube is arranged to supply coolant to the at least one accessory. | 12-18-2014 |
20140373555 | ACCESSORY MOUNTING FOR A GAS TURBINE ENGINE - A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. Frame is attached to the pylon at forward and rearward engine mounting locations. The frame includes at least one hollow tube and at least one hollow tube is fluid tight. The one hollow tube is evacuated or contains pressurised fluid and a pressure sensor is provided to detect a change in pressure in the at least one hollow tube to determine if there is a leak in the at least one hollow tube and hence if the frame is damaged. This ensures that the frame may be repaired or replaced before there is a loss of operation of one or more of the accessories which may result in a failure of the gas turbine engine. | 12-25-2014 |
20140373556 | SUPPORT STRUCTURE FOR A GAS TURBINE ENGINE - The present invention relates to a support structure ( | 12-25-2014 |
20150013344 | TUBE - The present disclosure relates generally to the field of tubes for carrying fluids. More specifically, the present disclosure relates to a tube having an oval shaped cross-section. In some embodiments, the tube with oval cross-section comprises a tube within a cavity in a gas turbine engine. | 01-15-2015 |
20150033759 | GAS TURBINE ENGINE COMPONENT - The invention concerns a gas turbine engine component ( | 02-05-2015 |
20150040579 | SYSTEM FOR SUPPORTING BUNDLED TUBE SEGMENTS WITHIN A COMBUSTOR - A system for supporting bundled tube segments within a combustor includes an annular sleeve that extends circumferentially and axially within the combustor, a support lug that extends radially inward from the annular sleeve and an annular support frame that is disposed within the annular sleeve. The annular support frame includes an inner ring portion, an outer ring portion and a plurality of spokes that extend radially between the inner and outer ring portions. The inner ring portion, the outer ring portion and the plurality of spokes define an annular array of openings for receiving a respective bundled tube segment. The inner ring portion is connected to each bundled tube segment and the outer ring portion is coupled to the support lug. | 02-12-2015 |
20150040580 | COMPRESSOR BLADE MOUNTING ARRANGEMENT - A compressor blade mounting arrangement includes a compressor blade having an airfoil, a base attachment and a platform disposed between the airfoil and the base attachment. The base attachment includes a first root portion extending radially inwardly from the platform and a second root portion extending radially inwardly from the platform, the first root portion and the second root portion defining a hollow portion therebetween. The base attachment also includes a compression plate disposed within the hollow portion and in fitted engagement with the first root portion and the second root portion. The base portion further includes at least one tab protruding from at least one of the first root portion and the second root portion. The compressor blade mounting arrangement also includes a wheel including a channel extending from a base wall to a rim of the wheel, the channel having a varying opening width. | 02-12-2015 |
20150075176 | CONNECTING GAS TURBINE ENGINE ANNULAR MEMBERS - A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively. | 03-19-2015 |
20150082806 | Micro-Mixer Fuel Plenum and Methods for Fuel Tube Installation - The present application provides a fuel plenum for a micro-mixer combustor. The fuel plenum may include a first assembly plate with a first assembly plate aperture, a second assembly plate with a second assembly plate aperture, a fuel tube extending through the first assembly plate aperture of the first assembly plate and the second assembly plate aperture of the second assembly plate, and an installation insert positioned between the fuel tube and the first assembly plate aperture. | 03-26-2015 |
20150082807 | CARRIER RING - The invention relates to a carrier ring for a high-pressure gas turbine of a gas turbine plant, which has a high-pressure combustion chamber upstream of the high-pressure gas turbine, a compressor upstream of the high-pressure combustion chamber, a low-pressure combustion chamber downstream of the high-pressure gas turbine, a low-pressure gas turbine downstream of the low-pressure combustion chamber, and a rotor that carries rotor blades for the compressor, for the high-pressure gas turbine, and for the low-pressure gas turbine. The carrier ring carries guide blades and/or heat shields of the high-pressure gas turbine and can be fastened to the high-pressure combustion chamber. The installation of the carrier ring can be simplified by segmenting the carrier ring at least in the area of the guide blades thereof and/or of the heat shields thereof in the circumferential direction, wherein the segmented carrier ring has at least two ring segments that carry the guide blades and/or the heat shields. | 03-26-2015 |
20150089957 | DEVICE FOR CONNECTING A FIXED PORTION OF A TURBINE ENGINE AND A DISTRIBUTOR FOOT OF A TURBINE ENGINE TURBINE | 04-02-2015 |
20150096304 | AIR ACCELERATOR ON TIE ROD WITHIN TURBINE DISK BORE - A gas turbine engine high pressure rotor with first and second high pressure turbine stages include first and second stage disks having first and second stage disk bores and a single tie rod therethrough. First and second bore annular flowpaths are radially located between first and second stage disk bores and tie rod. A means for increased cooling and/or heating in second stage disk bore is axially located within second stage disk bore. The means may include an airflow accelerator such as one or more annular ribs on the tie rod. A bore annular cross-sectional flow area between the second stage disk hub and the ribs may be substantially smaller than between the second stage disk hub and the tie rod. An axially unobstructed inlet into the second bore annular flowpath allows fully axially flowing and axially unobstructed flowing of second stage bore cooling air into inlet. | 04-09-2015 |
20150101344 | Systems and Methods for Bypassing a Coalescer in a Gas Turbine Inlet - A system including an air intake subsystem having a housing is provided. A coalescer having a frame is disposed inside the housing. The system includes a mounting bracket, and a release mechanism coupled to the frame and the mounting bracket. The release mechanism is adapted to selectively release the frame. | 04-16-2015 |
20150114003 | TRANSITION DUCT ASSEMBLY WITH MODIFIED TRAILING EDGE IN TURBINE SYSTEM - Transition duct assemblies for turbine systems and turbomachines are provided. In one embodiment, a transition duct assembly includes a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct assembly further includes an aerodynamic structure defined by the passages of the first transition duct and the second transition duct. The aerodynamic structure includes a pressure side, a suction side, and a trailing edge, the trailing edge having a modified aerodynamic contour. | 04-30-2015 |
20150114004 | GAS TURBINE ENCLOSURE - A gas turbine enclosure apparatus is provided and includes a frame defining an interior, gas turbine equipment disposed in the interior, the gas turbine equipment being pre-assembled at a first site and connectable with a gas turbine disposed at a second site and wall panels connectable with the frame. The apparatus being disposable proximate to the gas turbine such that the gas turbine equipment is exposed to the gas turbine and a portion of the wall panels form a portion of an outer enclosure of the gas turbine and the gas turbine equipment. | 04-30-2015 |
20150114005 | GAS TURBINE ENGINE - A gas turbine engine having a fan and a bypass duct for discharging airflow from the fan to generate engine thrust. The bypass duct includes a first component and a second component each having a gas washed surface, the first component being positioned adjacent the second component with a gap therebetween. A sealing strip is positioned in the gap between the first component and the second component distal to the gas washed surfaces of the first and second components. A sealant is positioned between the first and second component proximal to the gas washed surfaces of the first and second components, so as to seal the gap between the first component and the second component from airflow through the bypass duct. | 04-30-2015 |
20150121895 | FULL RING SLIDING NACELLE WITH THRUST REVERSER - A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion. | 05-07-2015 |
20150121896 | REVERSE CORE FLOW ENGINE MOUNTING ARRANGEMENT - A mounting arrangement for an aircraft engine includes a mounting structure attached to an aircraft body and not directly connected to an engine core of the aircraft engine, a propulsor mounted to the mounting structure, and a thrust reverser mounted directly to either the propulsor or mounting structure. | 05-07-2015 |
20150128609 | TRANSITION SUPPORT SYSTEM FOR COMBUSTION TRANSITION DUCTS FOR TURBINE ENGINES - An adjustable transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The adjustable transition duct support system includes an adjustable forward transition flexible support assembly in contact with a transition duct body, whereby the forward transition flexible support assembly may be formed from a base extending toward the transition duct body and first and second side support arms extending from the base to the transition duct body. The first and second side support arms may be formed from a plurality of flex plates spaced from each other with spacers that provide rigidity in circumferential and radial directions and flexibility in an axial direction. The number of flex plates used may be varied to accommodate different turbine engines. The adjustable transition duct support system may have natural frequencies for circumferential and radial modes above two engine orders. | 05-14-2015 |
20150135726 | Surface Cooler Support Mechanism - A surface heat exchanger is provided which utilizes forward and aft brackets to retain the heat exchanger in position. The surface heat exchanger includes a plurality of core cooling channels as well as fins which are disposed for air flow through the gas turbine engine. The brackets include a low-friction wear material as well as an isolator sheet which provides some spring force on the heat exchanger. | 05-21-2015 |
20150143813 | INDUSTRIAL GAS TURBINE EXHAUST SYSTEM WITH SPLINED PROFILE TAIL CONE - An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity. | 05-28-2015 |
20150143814 | INDUSTRIAL GAS TURBINE EXHAUST SYSTEM WITH AREA RULED EXHAUST PATH - An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity. | 05-28-2015 |
20150143815 | INDUSTRIAL GAS TURBINE EXHAUST SYSTEM WITH MODULAR STRUTS AND COLLARS - An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity. | 05-28-2015 |
20150143816 | MODULAR INDUSTRIAL GAS TURBINE EXHAUST SYSTEM - An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity. | 05-28-2015 |
20150308343 | INSTALLATION MOUNTS FOR A TURBINE EXHAUST CASE - A turbine exhaust case frame ( | 10-29-2015 |
20150308349 | FUEL DELIVERY SYSTEM - A fuel delivery system for a gas turbine combustor is provided. The fuel delivery system includes a fuel tube and an attachment assembly. The fuel tube extends from a downstream injector (e.g., a late lean injector) towards a mounting ring of the combustor and is moveably attached to the mounting ring using the attachment assembly. Accordingly, the exemplary fuel delivery system may provide fuel to a downstream injector while accommodating a thermal expansion or contraction of the fuel tube along an axial direction of the combustor. | 10-29-2015 |
20150321382 | Integral Ceramic Matrix Composite Fastener With Non-Polymer Rigidization - A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed. | 11-12-2015 |
20150322816 | GAS TURBINE ENGINE AND SEAL ASSEMBLY THEREFORE - The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least one beam. An anti-vibration seal is disposed in contact with beam and operative to mitigate an externally induced vibratory response of the beam. | 11-12-2015 |
20150345400 | FRAME JUNCTION COOLING HOLES - A module for a gas turbine engine comprises a frame and a frame cooling system. The frame includes a circumferentially distributed plurality of radially extending struts. Each strut is joined to an outer frame section at an outer frame junction, and joined to an inner frame section at an inner frame junction. The frame cooling system comprises an inlet, a plurality of cooling air passages extending from the inlet radially through each of the plurality of frame struts; and an outlet. The outlet is in fluid communication with at least one of the cooling air passages and includes a film cooling hole formed through the frame proximate the outer frame junction. | 12-03-2015 |
20150345404 | TURBINE SECTION OF HIGH BYPASS TURBOFAN - A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170. | 12-03-2015 |
20150345792 | GAS TURBINE ENGINE COMBUSTOR TOP HAT COVER ATTACHMENT SYSTEM WITH LUGGED INTERLOCKING BACKING PLATE - Combustor top hat covers are attached to midframe combustor portals with a lugged backing plate that interlocks with mating recesses formed in the corresponding midframe combustor portal. Exemplary embodiments utilize twist lock engagement of backing plate ring lugs under projecting tabs formed over a lug raceway recess in the combustor portal mating surface. The top hat cover is in turn fastened to the combustor portal by fasteners that engage corresponding threaded apertures formed in the backing plate. | 12-03-2015 |
20150345793 | FUEL NOZZLE ASSEMBLY WITH REMOVABLE COMPONENTS - A fuel nozzle assembly ( | 12-03-2015 |
20150354412 | COMPLIANT HEAT SHIELD LINER HANGER ASSEMBLY FOR GAS TURBINE ENGINES - Hanger assemblies for coupling heat shield liners to cases of gas turbine engines are disclosed. The disclosed hanger assemblies include a pivoting joint coupled between a first segment and a second segment. The first segment is coupled to the liner by a liner attachment assembly and the second segment is coupled to the case by a case attachment assembly. At least one of the liner attachment assembly or the case attachment assembly permits translational movement of the first or second segments respectively with respect to the liner or case to accommodate for thermal expansion in the axial direction. | 12-10-2015 |
20150354818 | MULTIPLE VENTILATED RAILS FOR SEALING OF COMBUSTOR HEAT SHIELDS - A seal for sealing a combustor heat shield against an interior surface of a combustor shell, the seal comprising: an upstream rail and an downstream rail defining an intermediate groove therebetween, each rail having a sealing surface with a plurality of slots extending between an upstream wall surface and a downstream wall surface, the sealing surface conforming to the interior surface of the combustor shell and defining a leakage gap therebetween. | 12-10-2015 |
20150354820 | COMBUSTOR WITH TILED LINER - A combustor for use in a gas turbine engine and methods for assembling the same are disclosed. The combustor includes an outer case and a combustion liner. The combustion liner is arranged radially inward of the outer case. The combustion liner is arranged to define an annular combustion chamber. | 12-10-2015 |
20150361892 | DUCT - The present invention provides a support duct for a gas turbine engine. The supported duct comprises at least one support frame having an aperture defined by an upper aperture wall, a lower aperture wall and opposing aperture side walls. It further comprises a duct extending through aperture, the duct comprising an upper panel in abutment with the upper aperture wall, a lower panel in abutment with the lower aperture wall and opposing side walls extending between the upper and lower panels. The opposing side walls of the duct are spaced from the opposing aperture side walls. | 12-17-2015 |
20150367949 | COWL WITH PRESSURE DRIVEN LATCH - A gas turbine engine includes an engine core, a core cowl extending circumferentially around the engine core, and a pressure actuated latch assembly. The core cowl includes a first cowl section on a first side of the engine core and a second cowl section on a second side of the engine core. The pressure actuated latch assembly connects the first cowl section to a support structure and is actuatable between an unlatched position when pressure within the core cowl is relatively low and a latched position when pressure within the core cowl is relatively high. | 12-24-2015 |
20150377068 | COMPONENT ARRANGEMENT FOR A GAS TURBINE - The present invention relates to a component arrangement for a gas turbine, having a first component of a gas turbine duct casing; a second component, connected to it, of a gas turbine duct casing with a flange; a rocker with an articulated section, which is rotatably mounted in a groove on the first component, which, in a cross section perpendicular to the groove longitudinal direction, has two groove flanks that lie opposite each other in the groove width direction, a groove base connecting these groove flanks, and a groove edge that lies opposite the groove base in a groove depth direction; and a setting screw. The flange of the second component is clamped between the first component and an arm of the rocker, which is tightened against the flange by the setting screw. | 12-31-2015 |
20160003069 | ADJUSTABLE TRANSITION SUPPORT AND METHOD OF USING THE SAME - A gas turbine engine including an adjustable transition assembly is disclosed. The gas turbine engine includes at least a combustor section and a turbine cylinder section, wherein the combustor section includes a transition piece coupled to a vane carrier assembly. The vane carrier assembly includes a plurality of holes that correspond with one or more holes of the transition piece, wherein at least one of the plurality of holes is adapted to receive a transition adjustable means therein for shifting the transition piece toward an upstream or downstream end. Also provided is a method for shifting a transition piece in a gas turbine engine, the method including at least the step of moving a transition adjustable means from a first position to a second position, where the movement shifts the transition piece in a direction towards an upstream end or a downstream end. | 01-07-2016 |
20160040543 | COMBUSTOR SLIDING JOINT - A sliding joint in a gas turbine engine between a large exit duct of a combustor and a turbine vane assembly having a leading edge lug. The sliding joint has an elongated flexible arm extending between a first end joined to the outer surface of the large entry duct, and an opposed free second end disposed radially inward of the outer surface of the large entry duct. A spacer is joined to the second end of the arm and projects radially away therefrom toward the outer surface of the large entry duct. The spacer is spaced apart from the outer surface and defines a gap therebetween. The spacer, the arm, and the sliding joint axially displace with respect to the lug upon thermal expansion of the large entry duct. | 02-11-2016 |
20160040878 | COMBUSTOR HEAT SHIELD SEALING - A method and an apparatus for reducing airflow leakage between a combustor liner and a rail of a heat shield mounted to an inner surface of the combustor liner. The method comprises locally deforming the combustor liner in sealing engagement with the rail by applying a pressure on the outer surface of the combustor liner over the rail of the heat shield. A tool, such as a sealing clip, may be mounted in pressing engagement with the outer surface of the combustor liner to apply forces locally on the liner over the rail of the heat shield. | 02-11-2016 |
20160053636 | Injection Molded Composite Fan Platform - A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface. A plurality of platform hooks may extend radially inwardly from the inner surface. | 02-25-2016 |
20160061449 | METHOD AND TOOL FOR INSTALLATION OF A TRANSITION DUCT - In a method for installation of a transition duct in a gas turbine engine, a guide structure is positioned that extends in an inclined direction with respect to a gas turbine axis. At least a portion of the guide structure is disposed between a turbine section and a combustor section of the gas turbine engine. The transition duct is engaged with the guide structure such that the transition duct is movable along the guide structure. Motion is imparted to the transition duct along the guide structure in a forward-to-aft direction, to move the transition duct to an installed position in which an aft end of the transition duct is aligned for attachment to a forward face of a stator component of the turbine section. | 03-03-2016 |
20160061450 | APPARATUS AND METHOD INCORPRATING A TRANSITION AFT SUPPORT FOR A GAS TURBINE ENGINE - An apparatus for supporting an aft portion of a transition duct in a gas turbine engine includes a transition aft frame that engages with an annular shaped stator component disposed in a turbine section of the gas turbine engine. The transition aft frame includes radially inner and outer panels and circumferentially spaced first and second side panels connecting the inner and outer panels. A forward face of the stator component includes first and second connection points circumferentially spaced apart. The transition aft frame includes first and second attachment structures that respectively engage with the first and second connection points when the transition duct is aligned axially with the stator component. The first and second attachment structures are spaced apart in a manner effective to transfer moment load from the first and second attachment structures to the first and second side panels respectively. | 03-03-2016 |
20160069570 | METHOD AND APPARATUS FOR CONDITIONING DIFFUSER OUTLET FLOW - A diffuser for a gas-turbine engine is provided. The diffuser has an outer housing, an inner housing, and a diffusion plate. The outer housing has a first wall. The inner housing has a second wall and is disposed within the outer housing. A flow passage is formed between the first wall and the second wall and has a forward end and an aft end. The diffusion plate has a plurality of openings and extends across the flow passage from the first wall to the second wall in an aft direction. | 03-10-2016 |
20160108817 | GAS TURBINE ENGINE SUPPORT STRUCTURES - A ducted fan gas turbine engine has a propulsive fan, a fan case surrounding the fan, a core engine, and a plurality of support structures which transmit loads from the core engine to the fan case. Each support structure has two support struts which extend from the core engine to a joint radially outwardly of the fan case. The support struts are spaced apart at the core engine but converge to meet at the joint. Each support structure further has two structural elements which extend from the joint to respective fixing positions on the fan case at opposite sides of the joint. | 04-21-2016 |
20160109135 | Liner Retaining Feature for a Combustor - The present application provides a combustor for use with a gas turbine engine. The combustor may include a liner and a flow sleeve surrounding the liner with the liner and the flow sleeve defining a flow path therebetween. A liner retaining feature extends into the flow path to retain the liner within the flow sleeve. The liner retaining feature may include a bolt therein. | 04-21-2016 |
20160131041 | TURBOMACHINE INCLUDING A TRANISTION PIECE TO TURBINE PORTION VARIABLE PURGE FLOW SEAL MEMBER - A turbomachine includes a compressor portion, and a turbine portion operatively connected to the compressor portion. The turbine portion includes a compressor discharge portion, a hot gas path and a first stage nozzle arranged at the hot gas path. A combustor assembly is fluidically connected to the compressor portion. A transition piece has an inlet portion fluidically connected to the combustor assembly and an outlet portion fluidically connected to the turbine portion. A seal member is operatively connected relative to one of the transition piece and the first stage nozzle of the turbine portion. The seal member extends from a first end to a second, cantilevered end through an intermediate portion including one or more openings that provide a purge fluid flow path from the compressor discharge portion toward the hot gas path. | 05-12-2016 |
20160153292 | FRAME SEGMENT FOR A COMBUSTOR TURBINE INTERFACE | 06-02-2016 |
20160153306 | RADIAL POSITION CONTROL OF CASE SUPPORT STRUCTURE WITH SPLINED CONNECTION | 06-02-2016 |
20160169113 | GAS TURBINE TRANSITION PIECE AFT FRAME ASSEMBLY SUPPORTS | 06-16-2016 |
20160177840 | AUXILIARY COMPONENT MOUNTS | 06-23-2016 |
20160201506 | TURBINE EXHAUST CYLINDER/ TURBINE EXHAUST MANIFOLD BOLTED STIFFENING RIBS | 07-14-2016 |
20160201517 | CAPTIVE COMPONENT ON A FASTENER | 07-14-2016 |
20160201567 | SYSTEM AND APPARATUS FOR DIVERSIFIED GEARBOX | 07-14-2016 |
20220136440 | GAS TURBINE ENGINE MOUNTED ABOVE WING AND WITH CAMBER - A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed. | 05-05-2022 |