| Entries |
| Document | Title | Date |
|---|
| 20080232962 | TURBOMACHINE AND METHOD FOR ASSEMBLY THEREOF USING A SPLIT HOUSING DESIGN - The present invention provides an improved design for turbomachinery, such as blowers and compressors, for providing pressurized process gas. The improved design comprises two housing portions that fit together to form an interior cavity in which a preassembled rotating assembly may be installed and balanced. Each housing portion includes an interior compartment designed and shaped to correspond to desired positions of components of the rotating assembly. After the preassembled rotating assembly is seated within the interior compartment of the lower housing portion and balanced, the upper housing portion can be fitted to the lower housing portion to complete the machine housing and encompass and hold the rotating assembly in place without the need to remove or disassemble the rotating assembly. A collector cover can thereafter be attached to the assembled machine housing to enclose an impeller operatively mounted on a rotating shaft of the rotating assembly. | 09-25-2008 |
| 20080240918 | Gear case assembly - A gear case assembly includes an upper gear case and a lower gear case accommodating a drive axle, at least one rotation axle receiving power from the drive axle, and a power transmission unit for transmitting the power to the at least one rotation axis. The upper and lower gear cases are horizontally divided, and upper and a lower shrouds are integrally formed on the upper and lower gear cases proximate to ends of the rotation axis. The upper and lower shrouds form a surface for guiding a fluid that flows from an impeller connected to the rotation axle, and are horizontally divided. Scroll cases mounted on the upper and lower gear cases, together with the upper and lower shrouds, define a path for guiding the fluid that flows from the impeller. A common plane divides the upper and lower gear cases, and also divides the upper and lower shrouds. | 10-02-2008 |
| 20080247869 | Combustion Air Supply Blower with Access Cover and Motor and Fan Assembly - A combustion air supply blower includes a blower housing having a housing body and housing cover. The cover is removably attached to the housing body and generally provides access to a motor and fan assembly including a fan and a motor. The motor and fan assembly is removably mounted within the housing body and is captured between the housing body and the housing cover such that, upon removal of the housing cover, the motor and fan assembly is exposed and may then be lifted out of the housing body for easy maintenance, repair, and/or replacement of any portion of the motor and fan assembly. Alternatively, upon removal of the housing cover, the motor and fan assembly may be accessed while remaining within the housing body to complete any maintenance and/or repair of the motor and fan assembly. | 10-09-2008 |
| 20080279683 | Liner retention system - Apparatus and method for securing a cylinder liner to a pumping module. A first part of an assembly housing pistons is fastened to a pumping module and a second part of the assembly is brought against the first so that the pistons act on tensioning plates which each have a stud rod extending therefrom through the assembly at an end distal to the pumping module. Each rod has a first portion substantially surrounded in an elastomeric member and a second portion threaded to receive a nut. The rods are passed through a clamping ring on the cylinder liner and the nut is attached to the rod. Actuating the pistons causes initial compression of the elastomeric member by the tension plate and allows tightening of the nut toward the pumping module. Release of the pistons then causes expansion of the elastomeric member to forcibly compel the cylinder liner towards the pumping module. | 11-13-2008 |
| 20080286100 | FAN BRACKET AND BRACKT SET - A fan bracket and a bracket set are respectively adapted to allow a cooling fan and cooling fans to be assembled therein. The cooling fan is provided with at least one positioning groove and the fan bracket includes a bracket body, at least one elastic positioning protrusion and at least one joint part, in which the bracket body is provided with at least one opening and used for allowing the cooling to be placed therein; the elastic positioning protrusion is disposed in the bracket body, corresponding to the positioning groove and used for lodging in the positioning groove to allow the cooling fan to be fixed in the bracket body; the joint part is disposed on one side face of the bracket body and used for connecting with a joint portion of a fixing element to enable the bracket body to be connected with and fixed on the fixing element. | 11-20-2008 |
| 20090010758 | Suspension arrangement for the casing shroud segments - A suspension arrangement for the casing shroud segments of the high-pressure turbine of a jet engine with inclination or graduation of the rotor blade tips ( | 01-08-2009 |
| 20090060733 | OVERLAP INTERFACE FOR A GAS TURBINE ENGINE COMPOSITE ENGINE CASE - A composite engine case with an axial interface. One configuration includes an alternating mix of full length and partial plies, in order to provide the total thickness needed for the axial overlap. Another configuration provides only full-length structural plies with a flyaway insert adjacent the axial interface. | 03-05-2009 |
| 20090060734 | Blower housing of hydrogen recirculation device of fuel cell vehicle - A blower housing of a hydrogen recirculation device for a fuel cell vehicle includes a plurality of cooling pins installed on a perimeter of a housing body installed in a fuel processing system of the recirculation device. The cooling pins are arranged in parallel with air flow, thereby reducing a temperature deviation and the highest temperature point. | 03-05-2009 |
| 20090081039 | GAS TURBINE ENGINE FRONT ARCHITECTURE MODULARITY - A gas turbine engine is disclosed that includes a spool having a compressor section. An inlet case is arranged axially upstream from the compressor section. A gearbox is secured to the inlet case. The gearbox couples the spool and a fan. A sealing assembly is arranged between the inlet case and the gearbox to provide a sealed bearing compartment. The inlet case, gearbox and seal assembly provide a module. A fastening element removably secures the module to the spool. The gas turbine engine can be serviced by disconnecting the fastening element from the engine core. The gearbox and inlet case can be removed as a module from the engine core without disassembling the gearbox. | 03-26-2009 |
| 20090123278 | STAGE OF A TURBINE OR COMPRESSOR, PARTICULARLY FOR A TURBOMACHINE - A stage of a turbine or compressor for a turbomachine, comprising at least a vane disk ( | 05-14-2009 |
| 20090123279 | CONNECTION OF RADIAL ARMS TO A CIRCULAR SLEEVE VIA AXES AND SPACERS - The connection assembly of an arm ( | 05-14-2009 |
| 20090123280 | TURBINE OR COMPRESSOR STAGE FOR A TURBOMACHINE - A turbine or compressor stage for a turbomachine, the stage comprising a blade wheel surrounded by a sectorized ring carried by a casing, each ring sector including a circumferential rim that is clamped radially a casing rail by two clamps of C-shaped section that are engaged on the circumferential end portions of the rim of the ring sector and on the corresponding portions of the casing rail. | 05-14-2009 |
| 20090136342 | Duct installation - A duct installation, for example a casing | 05-28-2009 |
| 20090155071 | SEALING A HUB CAVITY OF AN EXHAUST CASING IN A TURBOMACHINE - The exhaust casing of a turbomachine includes a cylindrical jacket for guiding a flow of exhaust gas and for defining a hub cavity inside the casing, the jacket including at its ends an annular flange and a radial annular portion extending inwards and formed with an annular rim that is designed to be received in an annular groove of the inner wall of the exhaust casing to close the hub cavity in substantially sealed manner. | 06-18-2009 |
| 20090175721 | COMBUSTOR SPRING CLIP SEAL SYSTEM - Aspects of the invention are directed to a sealing system for the interface between a combustor liner and transition duct. The system includes a spring clip seal. A first end of the spring clip seal operatively engages the inner peripheral surface of the transition duct. A second end of the spring clip seal is indirectly attached to the liner by an insert disposed therebetween. The spring clip seal can be attached to the insert by any kind of welding process that does not involve melting of the spring clip seal and the insert, such as fillet welding. The insert and the liner can be attached in a similar manner. Because fillet welds are relatively easy to cut, the spring clip, insert and liner can be separated without the need for cutting any of these individual components. Thus, the system can facilitate the repair, disassembly and reassembly of the interface. | 07-09-2009 |
| 20090214337 | AXIAL FLOW FAN UNIT - A fan frame includes a first housing having a first end portion in which a first protrusion is arranged, a second housing having a second end portion in which a second protrusion opposing the first protrusion along a specified axis is arranged, the second end portion being in an axially opposing relationship with the first end portion, and a fixing member attached to the first protrusion and the second protrusion to fix the first housing and the second housing together. Further, a first locking portion is arranged in the first end portion and a second locking portion engaging with the first locking portion is arranged in the second end portion. | 08-27-2009 |
| 20090238687 | BLOWER - A blower includes a housing unit, a fan blade unit, a driving device, a start capacitor, a switch device, and a power source device. The power source device is connected electrically to the switch device. The housing unit includes a driver housing for receiving the driving device, and a fan housing for receiving the fan blade unit. The driver housing includes a mounting recess. The housing unit further includes a cover plate for covering removably the mounting recess. The start capacitor and the switch device are disposed removably within the mounting recess, and are connected electrically to the driving device at the mounting recess. | 09-24-2009 |
| 20090269197 | Fan Assembly - A fan assembly for a gas turbine, the assembly comprising: a fan surrounded by a fan casing; a resilient, radially flexible containment material wrapped around the outside of the fan casing for containing a fan blade which has breached the casing during a fan blade-off event, and a retaining cable arrangement for resisting separation of a first portion of the casing from a second portion of the casing as a result of said breach occurring between the first and second portion; wherein the cable arrangement comprises: a retaining cable on the outside of the containment material, secured between the first and second portion of the casing, the retaining cable being sufficiently radially compliant for radial deflection to accommodate radial flexing of the containment material caused by impact of said fan blade inbetween the first and second portion; and a locking arrangement operable to subsequently lock the retaining cable between the front and rear portions of the casing whereby separation of the front and rear portions is resisted by tension in the locked cable. | 10-29-2009 |
| 20090285679 | ASYMMETRICAL MEMBER FOR LOCKING RING SECTORS TO A TURBINE ENGINE CASING - This invention relates to a locking member ( | 11-19-2009 |
| 20090324404 | Shear ring casing coupler device - A coupler device is for connecting first and second casings to form a casing assembly with a central axis, each casing having an inner end disposed against the inner end of the other casing such that the casings are spaced along the axis. The coupler device includes at least one generally arcuate connector having a first portion engageable with the first casing and a second portion engageable with the second casing so as to connect the two casings, the connector extending at least partially circumferentially about the casing axis. A retainer is disposeable either generally within or generally about the at least one connector and is configured to prevent radial displacement of the connector with respect to the axis so as to maintain engagement of the connector with the first and second casings. | 12-31-2009 |
| 20100040467 | TURBOCHARGER HOUSING WITH INTEGRAL INLET AND OUTLET OPENINGS - Exemplary embodiments of the present invention are directed towards a turbocharger for an internal combustion engine and more particularly an apparatus and method for fluidly coupling a turbocharger with an internal combustion engine. In one embodiment a turbocharger housing is provided. Turbocharger housing includes a turbine housing defining a volute chamber. The turbocharger housing also includes a first housing support extending from the turbine housing. The first housing support is integrally formed with the turbine housing and the first housing support defines an inlet opening and an outlet opening each of which are in fluid communication with the volute chamber. | 02-18-2010 |
| 20100054934 | EXHAUST GAS TURBOCHARGER - A turbocharger for a motor vehicle has a compressor housing, a turbine housing, a bearing housing, and at least one flange on the compressor side. The turbine housing is force-locked with the bearing housing by way of a fastening element that is arranged on the flange on the compressor side, thereby allowing the complete automatic assembly of the turbocharger. | 03-04-2010 |
| 20100098538 | Casing for a fluid flow machine - A casing of a fluid flow machine is provided. The casing includes two half-casings which abut against each other on an axial parting plane. The casing also includes a fastening device for fastening the two half-casings to each other and for pretensioning the two half-casings against each other. The fastening device includes at least one coil which wraps around the half-casings. The coil is made up of at least one tension cable having at least one wire. | 04-22-2010 |
| 20100143113 | Horizontally Split Flow Machine Housing - A horizontally split flow machine housing, particularly for a radial compressor, has a top housing part and a bottom housing part and a top stator part which is received in the top housing part and is prevented from falling out in that the top stator part is supported from the top by stator stops on housing stops. At least one housing stop is fastened to the top housing part in such a way that it can be adjusted toward a stator stop during assembly and is supported at the top housing part below a point of contact between the stator stop and housing stop. | 06-10-2010 |
| 20100226770 | ALIGNMENT DEVICE FOR GAS TURBINE CASINGS - In one embodiment, an alignment device may be configured to align a first turbine engine casing and a second turbine engine casing. The alignment device may include a fixed portion configured to be fixedly attached to the first turbine engine casing. The alignment device may also include a bridge portion configured to interface with the second turbine engine casing, wherein the bridge portion defines a first range of motion for the fixed portion along a first axis and a second range of motion for the fixed portion along a second axis when the alignment device is engaged with the first turbine engine casing and the second turbine engine casing, and wherein the alignment device is configured to facilitate movement of the first turbine engine casing relative to the second turbine engine casing within the range of motion and the second range of motion. | 09-09-2010 |
| 20100239419 | SLIDABLE COVER FOR CASING ACCESS PORT - A closure device for a casing having at least one access opening wherein the closure device includes a cover member movably disposed within an interior chamber of the casing so as to be slidably displaceable along or in the direction of a casing central axis between an open and a closed position, the cover member being spaced at least partially axially from the access opening in the open position so as to permit access to the interior chamber and generally extending across and substantially obstructing the at least one access opening in the closed position. | 09-23-2010 |
| 20100260601 | PATCH PLUG REPAIR OF A COMPRESSOR CASE STATOR RING HOOK, NEAR THE HORIZONTAL JOINT - A compressor case, and an associated method, repaired from damage to a segment of a stator ring hook. Two halves are engaged together at flange faces that define parting lines and that define a hollow interior, the ring hook being located at the interior, compressor case material having been removed at the stator ring hook location and a location of one of the flange faces to provide a space. A patch plug is slid into the space from the one flange face, the shape of the patch plug being complementary to a shape of the missing material space and inter-fitting therein, with an end of the patch plug being located at the one flange face to face an opposed half of the case with the two halves together. A fastener fastens the patch plug to the case and extending from the interior, through the patch plug, to the case. | 10-14-2010 |
| 20100260602 | INLET SECTION OF AN AIRCRAFT ENGINE NACELLE - A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange. | 10-14-2010 |
| 20100284806 | SIDE-OPENING JET ENGINE NACELLE - The invention relates to a nacelle including an air intake upstream from the jet engine ( | 11-11-2010 |
| 20100296925 | Housing Fastening Method - An object of the present invention is to provide, by contriving a housing structure, a housing fastening method and turbocharger capable of keeping down a reduction in fastening force applied by a G-coupling even when housings are exposed to high temperature. | 11-25-2010 |
| 20100296926 | GAS TURBINE AND METHOD FOR OPENING CHAMBER OF GAS TURBINE - A gas turbine includes a rotor rotated by combustion gas produced by a combustor that burns fuel, and a casing that is formed by connecting a plurality of casing members divided in plurality, the casing storing the rotor in an inside thereof, and including a second upper-side second vertical inner flange and a third upper-side first vertical inner flange for connecting a second upper casing member with a third upper casing member different from the second upper casing member among the casing members at the inside. | 11-25-2010 |
| 20110014044 | LOCKING SYSTEM FOR AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - The invention relates to a nacelle for a turbojet engine that comprises an air intake structure ( | 01-20-2011 |
| 20110038725 | COUPLING DEVICE INTENDED TO CONNECT FIRST AND SECOND ELEMENTS WHICH CAN MOVE RELATIVE TO ONE ANOTHER - The invention relates to a coupling device ( | 02-17-2011 |
| 20110070078 | Cover Assembly for Gas Turbine Engine Rotor - A cover assembly disposed about a rotor in a gas turbine engine. The cover assembly comprises a first cover, a second cover, and securing structure. The first cover is disposed about the rotor and comprises a forward end and an opposed aft end. The first cover is associated with a case mounting structure that is fixed to an engine casing. The second cover is disposed about the rotor and comprises a forward end and an opposed aft end. At least a portion of the first cover is disposed radially outwardly from the second cover. The securing structure couples the first cover to the second cover and permits relative radial movement between the first and second covers. | 03-24-2011 |
| 20110070079 | ANNULAR SEAL - An annular seal positionable in a gap is disclosed herein. The annular seal includes a plurality of leaves positioned about a center axis. Each leaf extends to a distal end that is elastically deflectable relative to the center axis to accommodate changes in a size of the gap. The annular seal also includes a ring encircling the center axis and at least partially interconnecting the plurality of leaves together for concurrent installation and removal. The annular seal also includes a plurality of tabs projecting from the ring along the center axis. Each of the tabs is directly connected to at least one of the plurality of leaves such that elastic deformation of one of the plurality of leaves induces bending in the corresponding tab before inducing bending in the ring. | 03-24-2011 |
| 20110070080 | FIXING APPARATUS FOR FAN - A fixing apparatus includes two receiving boxes, and a plurality of elastic members. The receiving boxes are covered to each other, to receive a fan. The plurality of elastic members is correspondingly fixed to the receiving boxes, to support the fan and separate the fan from the receiving boxes. When the fan operates, the plurality of elastic members absorbs vibration produced by the fan, and protects the fan from vibrating against the receiving boxes. | 03-24-2011 |
| 20110085904 | Divided Turbomachine Housing Having Optimized Parting Line Flanges - A turbomachine housing having a parting line is provided. The turbomachine housing has a first housing part with a first parting line bead, which is implemented on the parting line, a second housing part with a second parting line bead which is implemented on the parting line, and a plurality of parting line clamps. The first parting line bead is enclosed together with the second parting line bead by the parting line clamps, so that the first housing part and the second housing part are held together by the parting line clamps using a positive connection on the parting line beads. | 04-14-2011 |
| 20110103946 | LOCKING DEVICE - The invention relates to a locking device ( | 05-05-2011 |
| 20110158800 | LINER COUPLING PIN - A coupling pin for use in a pump housing, the pump housing including an outer casing and an inner pump liner, the coupling pin being suitable for locating the liner and casing relative to one another, the coupling pin including a shank and a head at one end of the shank. The head includes a cammed surface thereon which is adapted to co-operate with a follower on the liner, and a locating section on a remote or terminal end of the head which is adapted to be positioned against a seat in the outer casing when fitted. The arrangement is such that rotation of the coupling pin causes the follower to track along the cammed surface so as to cause relative movement between the outer casing and the inner pump liner. | 06-30-2011 |
| 20110158801 | FAN FRAME AND HEAT DISSIPATION APPARATUS USING THE SAME - A fan frame for a heat dissipation apparatus is provided. The fan frame includes an outer frame, an inner frame sleeved in the outer frame and slidable relative to the outer frame, a latching mechanism for mechanically securing the inner frame to the outer frame. The latching mechanism includes one or more resilient latches, one or more receiving portions capable of receiving the resilient latches in a first latched position and a second latched position, and an actuator mechanism connected to the outer frame and capable of resisting the resilient latch to cause elastic deformation of the resilient latch, thereby withdrawing the resilient latch from the receiving portion. | 06-30-2011 |
| 20110158802 | SHEAR RING CASING COUPLER DEVICE - A coupler device is for connecting first and second casings to form a casing assembly with a central axis, each casing having an inner end disposed against the inner end of the other casing such that the casings are spaced along the axis. The coupler device includes at least one generally arcuate connector having a first portion engageable with the first casing and a second portion engageable with the second casing so as to connect the two casings, the connector extending at least partially circumferentially about the casing axis. A retainer is disposeable either generally within or generally about the at least one connector and is configured to prevent radial displacement of the connector with respect to the axis so as to maintain engagement of the connector with the first and second casings. | 06-30-2011 |
| 20110171019 | LOCKING DEVICE COMPRISING A TELESCOPIC CONNECTING ROD EQUIPPED WITH RETURN MEANS - The present invention relates to a locking device ( | 07-14-2011 |
| 20110176918 | TURBINE - To provide a turbine that is capable of deforming (tilting) of a support portion (more specifically, a circular-truncated cone portion). A turbine that is provided with a vertically divided casing that is divided into two portions in a longitudinal direction and a support portion that supports a stator-blade ring disposed in the casing, wherein the support portion is provided with a flange portion that is secured between a joining surface of one portion of the casing and a joining surface of the other portion of the casing, being sandwiched therebetween, and a circular-truncated cone portion that connects the flange portion and a stator-blade holding ring, and wherein a thick plate portion having a greater plate thickness than the plate thickness of the flange portion and the stator-blade holding ring is provided between the flange portion located at a lower-half portion and the stator-blade holding ring. | 07-21-2011 |
| 20110182728 | NACELLE EQUIPPED WITH A DEVICE FOR DETECTING THE LOCKING STATE OF A LOCKING DEVICE - The present invention relates to a nacelle comprising a mid-section and an aft-section formed from two half-shells ( | 07-28-2011 |
| 20110200431 | JET ENGINE NACELLE WITH DAMPERS FOR HALF-SHELLS - The present invention relates to a jet engine nacelle ( | 08-18-2011 |
| 20110243727 | STEAM TURBINE HALF SHELL JOINT ASSEMBLY - A joint assembly for a steam turbine includes a threaded stud extending through mating openings in a first flange of the first half shell and in a second flange of the second half shell; a first nut threaded onto a first end of the threaded stud adjacent the first flange; a screw coupling the first nut to the first flange; and a dowel extending between and into the first flange and the first nut so as to bear a substantial portion of a torque load applied to the first nut compared to the screw. | 10-06-2011 |
| 20110250066 | Peripheral Control Ejector - A system for augmenting ducted fan thrust is provided, the system including a peripheral ejector comprised of inner and outer cowling members. With the addition of actuators mounted between the trailing edges of the inner and outer cowling members, the system may be used to generate control moments in the ducted fan. The peripheral ejector may be segmented to form discrete ejector control sections. | 10-13-2011 |
| 20110293414 | LOCKING DEVICE DESIGNED TO BE ARRANGED IN A JUNCTION REGION OF A NACELLE - The invention relates to a locking device ( | 12-01-2011 |
| 20120020782 | FAN CASE ASSEMBLY AND METHOD - A method for suspending a fan case and a fan case assembly in which a fan case is suspended are disclosed herein. The fan case assembly includes an inner ring encircling an axis. The fan case assembly also includes a first outer ring encircling the axis and having an annular flange. The fan case assembly also includes a plurality of struts each extending radially outward from an inner end engaged with the inner ring to an outer end engaged with the first outer ring. The fan case assembly also includes a second outer ring abutting the first outer ring along the axis. The fan case assembly also includes a plurality of leaves each fixed to the second outer ring and extending along the axis. The leaves are slid over an outer surface of the first outer ring to engage the first and second outer rings together. | 01-26-2012 |
| 20120027580 | FAN MODULE AND FAN RAIL THEREOF - A fan module and a fan rail thereof are provided. The fan module includes a fan, two fan rails and a holder. The fan rails are respectively disposed at opposite sides of the fan, and each of the fan rails includes a main body and a ring-pull, wherein the ring-pull has a tab portion and a pivot portion, and the pivot portion is pivoted with a first end of the main body. The fan is installed in the holder through the fan rails. The fan is adapted to be drawn out from the holder in an unlock state by rotating the tab portion of each of the fan rails along the pivot portion with respect to the main body and applying a pulling force to the tab portion. | 02-02-2012 |
| 20120027581 | REINFORCED CONCRETE GAS TURBINE OUTER CASE - A turbomachine outer case includes a pair of outer case sections, each provided with attachment flanges for securing said pair of outer case sections about an internal rotor structure, the pair of outer case sections constructed of a cement composite material. The outer case sections may be lined with a relatively thin metal alloy. | 02-02-2012 |
| 20120107113 | PUMP DEVICE - A pump device for applying a force opposing axial movement of a pump rotor shaft relative to a pump housing, the pump device having a first housing part, a second housing part axially moveable relative to the first housing part, and a biasing member coupled between the first housing part and the second housing part. | 05-03-2012 |
| 20120121408 | TURBINE TRANSITION COMPONENT FORMED FROM A TWO SECTION, AIR-COOLED MULTI-LAYER OUTER PANEL FOR USE IN A GAS TURBINE ENGINE - A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane. | 05-17-2012 |
| 20120148398 | BRUSH-TYPE SEAL FOR AN AIR-HANDLING UNIT - An air-handling unit including a housing with a discharge opening, and a fan disposed substantially within the housing. The fan includes a fan discharge that extends through the discharge opening thereby defining a gap between the fan discharge and the housing surrounding the discharge opening. A brush seal is coupled to one of the housing about the discharge opening and the fan discharge such that the brush seal extends across the gap forming a seal between the discharge opening and the fan discharge. | 06-14-2012 |
| 20120219415 | METALLIC ANNULAR CONNECTION STRUCTURE FOR AIRCRAFT TURBOMACHINE - A metallic annular connection structure between two parts for an aircraft turbomachine, with an arbitrary half-section including two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis, and two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction. The primary and secondary branches and the base of the first U are made in a single piece. | 08-30-2012 |
| 20120224959 | Latching Device for a Pump Housing and Pump - A latching device for a pump housing for production of a releasable latched connection between two housing parts has, on a first housing part, an elongate latching hook comprising a latching protrusion on the upper side and introduction chamfers on the upper side and on the underside. A latching opening is provided in the second housing part and comprises a latching tongue defining the latching opening outwardly, the latching protrusion abutting this latching tongue. An introduction web is arranged on the underside of the latching opening and comprises an introduction chamfer for the latching hook. Two securing tongues engage laterally in the latching opening and protrude via a free tongue end into the path of the latching hook when said latching hook is inserted into the latching opening. They prevent an undesired automatic release of the latched connection caused by movement of the latching hook in a downwards direction. | 09-06-2012 |
| 20120301291 | Tool for Removing Pins from a Gas Turbine Casing - A tool for removing a pin from a casing is disclosed. The tool may generally include a rod configured to be coupled to a portion of the pin, a sleeve received on the rod and a flange member received on the sleeve. The flange member may be received on the sleeve such that the flange member is movable in a radial direction relative to the sleeve. Additionally, the tool may include a collar configured to be radially engaged between the flange member and the rod when the flange member is moved radially outwardly relative to the sleeve. | 11-29-2012 |
| 20120308378 | Fluid Machine - Provided is a fluid machine which can be produced to have an increased weld strength and an increased reliability, at a reduced production cost. A first and a second shells ( | 12-06-2012 |
| 20130011253 | JOINT ASSEMBLY FOR AN ANNULAR STRUCTURE - A joint assembly for an annular structure comprises a first annular member having a first radially extending flange and a second annular member having a second radially extending flange. The first and second flanges having a plurality of first and second circumferentially aligned apertures. A plurality of fasteners are provided and each fastener is arranged to extend through a respective pair of the first and second apertures to join the first and second annular members together. The first and second radially extending flanges have a plurality of circumferentially aligned third and fourth apertures. A plurality of members are provided and each member is arranged to extend axially through a respective pair of the third and fourth apertures. | 01-10-2013 |
| 20130115079 | TIE-ROD NUT INCLUDING A NUT FLANGE WITH A PLURALITY OF MOUNTING APERTURES - A tie-rod nut includes a nut base that extends between a first nut end and a second nut end, and a nut flange that extends radially outwards from the nut base at the first nut end. The nut base includes a nut bore with a threaded bore region that extends axially from the second nut end towards the first nut end. The nut flange includes a plurality of mounting apertures that are arranged circumferentially around the nut base. The nut flange may be connected to a substrate by a fastener that extends through a first one of the plurality of mounting apertures. | 05-09-2013 |
| 20130129501 | STUD RETENTION - A gas turbine engine having two components attached together via a stud retention arrangement. The stud retention arrangement includes a stud having a shaft and an integral collar that is located between two engagement sections. A recess and a groove are defined in one of the components and an anti-rotation element; the collar defines a retention surface and is located within the collar recess, the anti-rotation element is located within the groove and engages the retention surface to prevent rotation of the stud during assembly of the components. | 05-23-2013 |
| 20130129502 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger (1) having a turbine housing (2), a compressor housing (3), a bearing housing (4) which has a bearing housing axis (L), and a connecting device (5) for connecting the bearing housing (4) to the turbine housing (2) and/or to the compressor housing (3). The connecting device has a multiplicity of screws (6), a number of screw holes (7, 7′) in the bearing housing (4) corresponding to the number of screws (6), and in the turbine housing (2) and/or in the compressor housing (3) a number of threaded holes (8) corresponding to the number of screws (6). The screw holes (7, 7′), the threaded holes (8) and the screws (6) are arranged at an acute angle (α) with respect to a joining surface (9) between the bearing housing (4) and the turbine housing (2) or between the bearing housing (4) and the compressor housing (3). | 05-23-2013 |
| 20130142643 | STRUCTURAL JOINT FOR CONNECTING A FIRST COMPONENT TO A SEGMENTED SECOND COMPONENT - A structural joint includes a first flange, a second flange and a fastener with a head and a shaft. The first flange extends out from a first component to a distal first flange end. The second flange extends out from a segmented second component to a distal second flange end. The second flange includes a first lateral flange segment that extends laterally to a first flange sidewall, and a second lateral flange segment that extends laterally to a second flange sidewall, which is engaged with the first flange sidewall. The head is encased in the second flange and extends laterally into the first flange sidewall and the second flange sidewall. The shaft extends longitudinally out from the second flange and through the first flange. | 06-06-2013 |
| 20130149139 | DYNAMIC LOAD REDUCTION SYSTEM - Bolted together first and second flanges include bolts disposed through first bolt holes in the first flange. The bolts extend at least partially through second holes in the second flange. Bolt include bolt heads, threads, and shanks therebetween. Crushable spacers disposed around the shanks of a first plurality of the bolts and contacting and axially extending between the bolt heads and the first flange. Bushings disposed around a second plurality of the bolts and contacting and axially extending between the bolt heads and the second flange. A shank outer diameter may be smaller than a thread diameter and heat shrink tubing may be disposed around the bolt shanks of at least some of the spacers. First bolt holes may extend into an open annular slot on first flange and second holes may extend partially through a forward extending annular rail of second flange with rail received within slot. | 06-13-2013 |
| 20130183150 | COMPONENT OF A TURBINE WITH LEAF SEALS AND METHOD FOR SEALING AGAINST LEAKAGE BETWEEN A VANE AND A CARRIER ELEMENT - A component of a turbine includes a vane, a carrier element and at least four interfaces between the vane and the carrier element. The at least four interfaces are sealed via leaf seals. A method for sealing against leakage between a vane and a carrier element of the above-mentioned turbine component includes sealing the at least four interfaces by way of leaf seals | 07-18-2013 |
| 20130202430 | GAS TURBINE ENGINE FAN CASING HAVING A FLANGE FOR FASTENING PIECES OF EQUIPMENT - The invention provides a fan casing for a gas turbine engine, the casing having a substantially cylindrical portion that terminates at one end in an annular flange made of composite material. The flange includes at least one setback in a fraction of its thickness and at least one bolt for fastening pieces of equipment passing right through the flange in the axial direction, the bolt for fastening pieces of equipment having a head that presents a flat that is to bear flat against a rim of the setback, and a shank forming a stud for fastening pieces of equipment on the casing. | 08-08-2013 |
| 20130209250 | TRANSITION PIECE SEAL ASSEMBLY FOR A TURBOMACHINE - A transition piece seal assembly includes a first seal, and a second seal joined to the first seal. The second seal being spaced from the first seal to define a coolant passage. | 08-15-2013 |
| 20130216375 | EXHAUST-GAS TURBOCHARGER AND METHOD FOR MANUFACTURING THE SAME - An exhaust-gas turbocharger ( | 08-22-2013 |
| 20130272870 | MICA-BASED SEALS FOR GAS TURBINE SHROUD RETAINING CLIP - A gas turbine, a gas turbine shroud, and a method for sealing a gas turbine shroud with a non-metallic seal are provided. The gas turbine shroud includes an inner shroud and an outer shroud. A non-metallic seal is located between the inner shroud and the outer shroud while a shroud retainer clip applies a compression force upon the inner shroud and the outer shroud. The compression force compresses the non-metallic seal to fill a gap space between the inner shroud and the outer shroud to control fluid flow between a flow path and a non-flow path. | 10-17-2013 |
| 20130287565 | TEC Mount Redundant Fastening - A mounting apparatus for a turbine exhaust case (TEC) is provided. The mounting apparatus may include a neck, support links and a plurality of fastening pins. The neck may include an upper portion that is receivable within a pylon associated with the TEC and at least one neck aperture extending therethrough. The support links may downwardly extend from a lower portion of the neck. The support links may be configured to at least partially receive a section of the TEC. Each support link may include at least one link aperture extending therethrough. The fastening pins may include at least one neck pin extending through the neck aperture and at least one link pin extending through the link aperture of each support link. | 10-31-2013 |
| 20130294907 | TUBULAR HOUSING FOR A TURBOMACHINE - A tubular housing for a turbomachine is provided. The tubular housing includes two half-tube shells which, lying against one another in two connecting regions overlap partially in each case in the tangential direction of the tubular housing. In order to specify a particularly reliable and permanent connection of the two half-tube shells which additionally develop a particularly satisfactory sealing action, it is proposed that, in order to interlock the half-tube shells in the tangential direction, in relation to the tube axis of the housing, at least one eccentric pin is provided in one or both connecting regions. | 11-07-2013 |
| 20130302158 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 11-14-2013 |
| 20130309085 | COMPRESSOR CASE OVERHAUL - A longitudinally-split compressor case of a gas turbine engine is overhauled to inhibit leakage between case segments that have been distorted. Grooves are machined in mating surfaces of the case segments. Seal wires are located at the grooves. | 11-21-2013 |
| 20140037445 | TURBINE SHELL WITH PIN SUPPORT - A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell. | 02-06-2014 |
| 20140044538 | CLAMPING RING FOR A TURBOMACHINE - A turbomachine having a flow channel ( | 02-13-2014 |
| 20140044539 | MOLDED PART - An additional pad | 02-13-2014 |
| 20140056704 | TURBINE ENGINE SUPPORT ASSEMBLY INCLUDING SELF ANTI-ROTATING BUSHING - A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component. | 02-27-2014 |
| 20140064957 | GAS TURBINE FAN CASING HAVING A BELT FOR FASTENING EQUIPMENT - The invention relates to a gas turbine fan casing ( | 03-06-2014 |
| 20140079545 | FAN ASSEMBLING STRUCTURE AND FAN DEVICE HAVING THE SAME - The disclosure provides a fan assembling structure and a fan device having the same. The fan comprises a frame having an upper board, a lower board and a circular connector, and blades disposed in the frame. The lower board comprises four side edges in sequential connection. A first fixing hole is at the first side edge, and a second fixing hole is at the upper board. The structure comprises an assembling board having a bottom plate and two parallel side plates. The bottom plate comprises a ventilating area. A through hole is defined at a first side of the ventilating area, and a hook is disposed on a second side of the ventilating area. And at least one protrusion extends inwardly from an inner side of at least one of the two parallel side plates, a guiding slot being formed between the protrusion and the bottom plate. | 03-20-2014 |
| 20140093370 | GAS TURBINE ENGINE COMBUSTOR LINER - A wrenching mechanism includes a multiple of rectilinear fastener plates each with a nut-shaped opening, each of the multiple of rectilinear fastener plates located within one of the multiple of rectilinear openings. A fastener mounted at least partially through the nut-shaped opening of each of the multiple of rectilinear fastener plates. | 04-03-2014 |
| 20140093371 | MID-TURBINE FRAME HEAT SHIELD - A heat shield for a mid-turbine frame has a conical body, including at least one axial retention feature, at least one circumferential retention feature, and at least one radial retention feature. | 04-03-2014 |
| 20140099198 | DUCT ASSEMBLY - A duct for a gas turbine engine system is used to convey exhaust gas and bypass air away from the engine system, towards an exhaust nozzle. The duct includes an inlet face having at least two inlet portions and defines the outer extremity of a path for the gas and/or air through the duct. The duct includes a plurality of flat panel members which together define the outer extremity of the path. | 04-10-2014 |
| 20140112771 | FAN ASSEMBLING STRUCTURE AND HEAT DISSIPATING DEVICE - The invention provides a fan assembling structure and a heat dissipating device. The fan assembling structure comprises a first assembling board for assembling a fan thereon and a second assembling board connected to the first assembling board, the fan comprising a frame and blades disposed in the frame assembled to the first assembling board, the frame having an upper board, a lower board and a circular connector connected between the upper board and the lower board, the lower board including a first side edge, a second side edge, a third side edge and a fourth side edge in sequential connection. | 04-24-2014 |
| 20140119910 | TURBINE EXHAUST HOOD AND RELATED METHOD - A turbine exhaust hood and related method of installation is disclosed. In one embodiment, the turbine exhaust hood includes: a housing having an end wall, the end wall including a first portion of a releasable coupling, and a first radially inner steam guide structure disposed within the housing, the first radially inner steam guide structure including a second portion of the releasable coupling, integral with a first end of the first radially inner steam guide structure. The first portion and the second portion of the releasable coupling releasably couple the first radially inner steam guide structure to the end wall. | 05-01-2014 |
| 20140133977 | DEVICE FOR CONNECTING A FRONT FRAME TO A FAN CASING - A device for connecting a front frame of a turbojet engine nacelle to a fan casing includes a locking pin connected to a first assembly flange and a retaining flange that is movably mounted and has at least one opening. In particular, the locking pin has a shank passing through an orifice of a second assembly flange secured to the fan casing. The opening is crossed through by the shank of the locking pin and interacts with an end groove of said locking pin. When the retaining flange is in the unlocking position, the opening has dimensions larger than those of the shank of the locking pin, and when the retaining flange is in the locking position, the opening has dimensions larger than a thickness of the locking pin at its groove but smaller than an overall thickness of the shank of the orifice of the second flange. | 05-15-2014 |
| 20140140839 | TURBINE CASING WITH SERVICE WEDGE - A turbine casing is provided and includes first and second turbine casing shells configured to be removably coupled to one another. At least one of the first and second turbine casing shells is formed to define an access slot. At least one service wedge is configured to be removably installed in the access slot. | 05-22-2014 |
| 20140147270 | Aircraft Nacelle Comprising A Reinforced Connection Between An Air Intake And A Means Of Propulsion - An aircraft nacelle includes an air intake, connected to a means of propulsion, which defines a longitudinal direction, an outer wall, an inner duct including an annular flange connected, by means of connecting elements, to the means of propulsion, and a forward frame and a rear frame which connects the outer wall and the inner duct. | 05-29-2014 |
| 20140169959 | SEALING SYSTEM FOR FLANGED JOINT - A sealing system is provided for a flanged joint. The sealing system includes a split seal and a spring. The split seal includes a radial outer surface, an axial outer surface, and a chamfered surface inclined with respect to the radial outer surface and the axial outer surface. The spring is disposed in urging contact with the chamfered surface and configured to apply an axial force, and a radial force on the axial outer surface, and the radial outer surface respectively. | 06-19-2014 |
| 20140255183 | TWIST PREVENTION FOR TURBOMACHINERY - A twist prevention system for turbomachinery is disclosed. The twist prevention system has a first ring segment pair with a first radially inner ring segment and a first radially outer ring segment and a second ring segment pair having a second radially inner ring segment and a second radially outer ring segment. The ring segment pairs have mutually facing faces. A portion of the face of the first radially inner ring segment overlaps a portion of the face of the second radially outer ring segment in the radial direction. | 09-11-2014 |
| 20140294581 | GAS TURBINE ENGINE ACCESS PANEL - An integrated access panel is disclosed that can be used to assist in adjusting a component like a fan blade of a turbofan engine. in one form the integrated access panel is hinged at one end such that the panel remains attached during adjustment of the fan blade. The access panel can be positioned in an angled flow surface of a nacelle such that the fan blade cannot be removed from a wheel without removal of the nacelle or opening of the access panel. The integrated access panel can be spring-loaded and positioned to allow the fan blade to be removed from a wheel by moving the access panel out of the way. Subsequent blade removal can occur by rotation of the wheel to locate another blade in proximity to the access panel. | 10-02-2014 |
| 20140341731 | PISTON SEAL RING - A gas turbine having a device and a further device is provided. The device includes an outer casing, an inner casing and a seal ring. The outer casing and the inner casing are arranged in such a way that a cooling duct is formed between each other. The seal ring is arranged between the outer casing and the inner casing in such a way that the seal ring seals the cooling duct from an environment surrounding the outer casing. The device and the further device are mounted together such that working fluid is flowable from the further device to the device. Furthermore the device includes a rotatable shaft and the further device includes a further rotatable shaft, wherein the rotatable shaft and the further rotatable shaft are mechanically decoupled from each other, and wherein the seal ring exclusively abuts against the inner casing and against the outer casing of the device. | 11-20-2014 |
| 20150016988 | SEAL FOR A HIGH-PRESSURE TURBOMACHINE - An annular seal is provided for use in a turbomachine. The annular seal may form a generally rectangular cross-section and may include an outer radial surface forming an outer sealing surface and defining at least one annular groove and a plurality of slots spaced circumferentially about the outer radial surface. Each slot may have an end terminating in the at least one annular groove. The annular seal may also include a first axial sidewall forming a sidewall sealing surface and a recessed portion and a second axial sidewall opposing the first axial sidewall. At least one annular groove and the plurality of slots may be configured to maintain a low pressure environment across at least a portion of the outer radial surface. The second axial sidewall, the recessed portion, and the inner radial surface may be configured to maintain a high pressure environment there across during operation of the turbomachine. | 01-15-2015 |
| 20150016989 | AXIAL FLOW FAN - An axial flow fan is provided. The axial flow fan includes an impeller and a fan frame. The impeller has a maximum outer diameter. The fan frame includes a first body and a second body. The first body includes a plurality of connecting elements and a base. The connecting elements are connected to the base. The second body is a hollow body, and used for disposing around the impeller. The second body includes a flow passage having a minimum inner diameter. The minimum inner diameter of the flow passage is not larger than the maximum outer diameter of the impeller. Therefore, the size of the second body does not restrict the maximum outer diameter of the impeller, and the shape of the impeller and the shape of the fan frame can be designed flexibly according to the practical demand. | 01-15-2015 |
| 20150030444 | TURBOMACHINE WITH GAP ADJUSTMENT - A turbomachine, in particular, a compressor, having a housing and having at least one housing insert accommodated therein and having a fitting piece for the adjustment of a gap dimension between the housing and the housing insert, wherein the housing comprises, for the adjustment of the gap dimension, a horizontally adjustable guide element into which the fitting piece is inserted, is provided. | 01-29-2015 |
| 20150044043 | ATTACHMENT DEVICE FOR NON-PERMANENTLY ATTACHING A CHILD COMPONENT TO A PARENT COMPONENT - The attachment device has a first elongate element for non-permanently attaching the child component to the parent component; a second elongate element; a holder. The holder is configured to rest against an installation surface of the parent component whilst holding the first and second elongate elements in position relative to the installation surface of the parent component such that: the first elongate element extends, from a first position on the installation surface of the parent component, entirely through the parent component and at least partially through the child component in a manner that permits the first elongate element to be used to non-permanently attach the child component to the parent component; the second elongate element extends, from a second position on the installation surface of the parent component that is different from the first position on the installation surface of the parent component, at least partially through the parent component. | 02-12-2015 |
| 20150050139 | PANEL ATTACHMENT SYSTEM - A gas turbine engine exhaust panel mounting system comprising a panel, a casing and an attachment assembly for removably connecting the panel to the casing comprises a retaining portion, a clamping portion, and a ‘C’-shaped connecting link. | 02-19-2015 |
| 20150056070 | MULTI SURFACE BLOCKER DOOR SYSTEM AND APPARATUS - A multi-surface blocker door system for a thrust reverser of an aircraft is provided. The system may comprise one or more first blocker doors coupled to the inner fixed structure. The first blocker doors may be configured to obstruct a fan duct area adjacent the engine. The system may also comprise one or more second blocker doors coupled to a translating sleeve. The second blocker doors may be configured to obstruct a fan duct area adjacent to an inlet of the nacelle. | 02-26-2015 |
| 20150078892 | ECCENTRIC COUPLING DEVICE AND METHOD FOR COUPLING MATING CASINGS IN A TURBOMACHINE - Turbomachines, coupling devices and methods for coupling a first casing and an second casing together are provided. The first casing and second casing include mating bore holes defined in mating flanges thereof, which may be misaligned. The coupling device may include a bushing insertable and positionable within one of the mating bore holes, and a pin insertable and positionable within the bushing and the other of the mating bore holes. The bushing and pin may each include eccentric features which may facilitate insertion into the mating bore holes when the bore holes are misaligned, thus coupling the first casing and second casing together. | 03-19-2015 |
| 20150086355 | RETAINING CLIP AND METHODS FOR USE IN LIMITING RADIAL MOVEMENT BETWEEN SECTIONS OF A SPLIT FAIRING - A retaining clip for use in limiting radial movement between a first section and a second section of a split fairing is provided. The first section includes a first clip tab and the second section includes a second clip tab extending therefrom, wherein the first and second clip tabs form a slot when the first section and the second section are substantially aligned. The retaining clip includes a first portion sized for insertion into the slot, a third portion coupled to the first and second clip tabs such that the first and second clip tabs are positioned between the first portion and the third portion, and a second portion extending between the first portion and the third portion. | 03-26-2015 |
| 20150098816 | SYSTEM AND METHOD FOR CONTROLLING BACKBONE BENDING IN A GAS TURBINE ENGINE - A flexible coupling for a gas turbine engine includes a fan hub frame having a first flange and a core engine having a second flange. The first flange includes a first plurality of fingers extending from a face of the flange and the second flange includes a second plurality of fingers extending from a face of the second flange. The second plurality of fingers of the second flange is complementary to the first plurality of fingers extending from the first flange. The first flange and the second flange are coupled together in form-fitting engagement such that the first plurality of fingers and the second plurality of fingers form an interdigitated configuration. | 04-09-2015 |
| 20150110620 | SEAL ARRANGEMENT - A seal arrangement ( | 04-23-2015 |
| 20150118042 | METHOD AND SYSTEM FOR PROVIDING SEALING IN GAS TURBINES - A gas turbine system is provided that includes a compressor section, a combustor assembly coupled to the compressor section, and a turbine section coupled to the compressor section. At least one of the combustor assembly and the turbine section includes a sealing sub-system for use in sealing between a first component and a second component. A first component defines a first seal member receiving region oriented between a higher-temperature gas region and a cooler-temperature gas region. A second component adjacent the first component defines a second seal member receiving region oriented adjacent the first seal member receiving region. The sealing system includes first and second end walls defined in at least one of the first and second seal member receiving regions. A seal member is oriented within the first and second seal member receiving regions, and includes at least a first layer defining at least a first resilient seal end portion that engages one of the first and second end walls. | 04-30-2015 |
| 20150139794 | COUNTER PLATE AND TURBO MACHINE COMPRISING A COUNTER PLATE - A counter plate for a turbo machine, including: a first external surface and a second external surface, which are substantially parallel; the first external surface of the counter plate creates a continuous ring or continuous ring segment and includes a first series of holes through which fasteners can pass; the second external surface of the counter plate including a plurality of surfaces for supporting heads of the fasteners, the support surfaces including a second series of holes, positioned facing the first series of holes, so that the fasteners can pass through the holes in the counter plate. | 05-21-2015 |
| 20150292360 | PANEL CONNECTION SYSTEM AND A METHOD OF USING THE SAME - A panel connection assembly connects a panel to a casing including hanger, first locating, and second locating plates. The hanger plate has elongate body, first end, and opposite second end portions, with each of the first and second end portions having a circular profile. The hanger plate has a dumbbell shape. The first locating plate has a first circular locating aperture, the first locating aperture to accommodate the first end portion, and the second locating plate has a second circular locating aperture, the second locating aperture to accommodate the second end portion. In use, the first locating plate is secured to the casing, the second locating plate is secured to the panel, the first and second end portions are respectively accommodated within the first and second locating apertures with the elongate body portions extending therefrom, to connect the panel to the casing. | 10-15-2015 |
| 20150300204 | TURBOJET ENGINE NACELLE WITH DOWNSTREAM SECTION - A turbofan engine nacelle has a downstream section which includes at least one front frame. The front frame is attached to a stationary portion of the nacelle, and the downstream section is provided with at least one rail or slide which extends in a longitudinal direction of the nacelle and is capable of engaging with at least one corresponding slide or rail of an attachment pylon of the turbofan engine. The front frame is connected to the rail or slide of the downstream section by means of at least one swiveled connecting rod. | 10-22-2015 |
| 20150300365 | IMPROVED SEAL SYSTEM FOR CENTRIFUGAL PUMPS HAVING AXIALLY SPLIT CASINGS - Disclosed invention is an improved sealing system for axially split, centrifugal pumps. The improved sealing system eliminates the need for a gasket between casing halves. In the improved sealing system, a fluid tight seal is provided by an elastomeric cord positioned within a groove carried by the flange of at least one half of the axially split pump casing. | 10-22-2015 |
| 20150300370 | FAN FRAME AND ASSEMBLING METHOD THEREOF - A fan frame includes a first frame and a second frame. The first frame includes at least a first sidewall and a first connecting element, wherein the first connecting element is disposed on the first sidewall. The second frame includes at least a second sidewall and a second connecting element, wherein the second connecting element is disposed on the second sidewall and at least partially overlapped with the first connecting element. The second connecting element includes a first end and a second end in a first direction, wherein the first end and the second end are bent toward the first connecting element, respectively, for grasping the first connecting element. As a result, the accuracy error and the precision error are avoided, the stresses are internally counterbalanced, and the deformation of the fan frame is avoided. | 10-22-2015 |
| 20150308289 | ATTACHMENT OF A DISCHARGE CONDUIT OF A TURBINE ENGINE - Discharge conduit for a turbine engine, comprising an air intake end, an air outlet end and a tubular sleeve for guiding air between said ends, said air intake end being equipped with means for attachment to an intermediate casing of the turbine engine, characterized in that said attachment means are of the resilient snap-in type. | 10-29-2015 |
| 20150315925 | GAS TURBINE SEAL ASSEMBLY AND SEAL SUPPORT - A gas turbine engine assembly includes a second module interconnected with a first module along a joint such that a surface of a second radial wall faces a surface of a first radial wall, with a cavity defined in part by the first and second radial walls. A seal assembly includes a finger seal, and a seal support ring having a backing ring portion and a flow discourager arm. The backing ring is secured to one of the first radial wall and the second radial wall, and the flow discourager arm extends axially through the cavity into a recess formed in the other of the first and second radial walls. The finger seal includes a free end contacting an inner side of the flow discourager arm. | 11-05-2015 |
| 20150322967 | EVAPORATING FAN CASE FIXING SYSTEM FOR A REFRIGERATOR - The present invention pertains to a fan assembly for a refrigerator. Said assembly comprises a fan with a first and a second outer wall at two ends along axial direction of said fan. Said outer walls extend perpendicular to said axial direction of said fan. Said fan assembly comprises a wall element which delimits an evaporator within said refrigerator. Said wall element has a fan mounting opening with projecting edges in the direction of said fan, said fan assembly further comprising an isolator and a locking element. | 11-12-2015 |
| 20150337685 | METHOD AND DEVICE FOR MOUNTING AND REMOVING A TURBINE COMPONENT - The disclosure pertains to a mounting arrangement for installing and removing a turbine component. The mounting arrangement has a base cage, a main cage, and an inner structure. The base cage includes an interface for connection to a casing of the turbine, and an interface for connection to the main cage. The main cage includes an inner structure interface for movable connection to the inner structure. The inner structure is arranged at least partly inside the main cage and the inner structure interface is configured to allow a movement of the inner structure along a defined trajectory in the main cage. The inner structure includes a first face of a component interface for holding the turbine component. The disclosure further refers to a method for mounting and removing a turbine component. | 11-26-2015 |
| 20150345333 | INTERMEDIATE CASING EXTENSION OF IMPROVED DESIGN - The invention relates to an extension ( | 12-03-2015 |
| 20150345503 | SEALING ARRANGEMENT FOR AXIALLY SPLIT TURBOMACHINES - An axially-split turbomachine comprising a casing comprised of a first casing portion and a second casing portion, forming a housing for a rotor arranged for rotation therein. The rotor comprises a shaft and at least one impeller mounted on the shaft. The casing comprises at least one shaft passageway through which the shaft extends from the interior of the casing towards the exterior of the casing. The sealing arrangement comprises a linear sealing member, extending between the first and the second casing portions. The sealing arrangement further comprises at least one sealing ring portion surrounding said at least one shaft passageway. The sealing ring portion and the linear sealing member form a continuous sealing body. | 12-03-2015 |
| 20150361812 | CUTBACK AFT CLAMP RING - An aft clamp ring for a gas turbine engine is disclosed. The aft clamp ring includes a body, a forward sealing face, and an aft sealing face. The body includes an annular shape extending between an outer end and an inner end. The forward sealing face faces in a second axial direction. The aft sealing face is adjacent the outer end facing in a first axial direction and is at least partially radially aligned with the forward sealing face. The forward sealing face and the aft sealing face are each an annular surface with a surface area from 105.50 cm | 12-17-2015 |
| 20150369083 | LATCHING ACTUATION MECHANISM FOR NACELLE MOUNTED LATCHING SYSTEM - An assembly for a gas turbine engine includes a first fan cowl pivotable on a hinge from a first position to a second position. A latching actuation mechanism is disposed under the nacelle, engages the hinge, and is actuated by movement of the hinge between the first position and the second position. | 12-24-2015 |
| 20160017730 | METHOD AND APPARATUS FOR ATTACHING A TRANSITION DUCT TO A TURBINE SECTION IN A GAS TURBINE ENGINE - An apparatus for attaching a transition duct to a turbine section of a gas turbine engine includes an annular shaped vane carrier that engages with a transition aft frame. The transition aft frame includes an outwardly extending clamp that is at least partially inserted into a radial recess of the vane carrier structure. A spacer is inserted into the recess. A first pair of mating surfaces is formed by a first end face of the spacer and an end face of the clamp and a second pair of mating surfaces is formed by a second end face of the spacer and a wall of the recess. At least one of the pairs of mating surfaces is inclined at an angle with respect to a radial plane of the vane carrier structure. A retention device secures the spacer to the vane carrier structure. | 01-21-2016 |
| 20160017738 | ASSEMBLY FOR SEALING A GAP BETWEEN COMPONENTS OF A TURBINE ENGINE - An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a seal assembly. The first component includes a groove and a groove surface. The second component includes a tongue that extends into the groove to a tongue surface. The seal assembly at least partially seals a gap between the groove surface and the tongue surface. The seal assembly includes a rope seal and a clip that attaches the rope seal to the tongue. The rope seal is arranged within the groove between the groove surface and the tongue surface. | 01-21-2016 |
| 20160024951 | FLEXIBLE LAYERED SEAL FOR TURBOMACHINERY - The present application provides seal assemblies having improved flexibility for reducing leakages between adjacent misaligned components of turbomachinery. The seal assemblies include a first outer shim formed of a flexible permeable material and a second outer shim formed of a substantially impervious material. At least the second outer shim is configured for sealing engagement with seal slots of the adjacent components. The seal assemblies may also include at least one of an inner shim and a filler layer positioned between the first and second outer shims. The seal assemblies may be sufficiently flexible to account for misalignment between the adjacent components, sufficiently stiff to meet assembly requirements, and sufficiently robust to meet operating requirements associated with turbomachinery. A turbomachine including the seal assembly is provided. | 01-28-2016 |
| 20160032777 | COMPONENT ARRANGEMENT OF A GAS TURBINE - The present invention relates to a component arrangement of a gas turbine, this arrangement having a first gas turbine component, in particular a first wall segment (10) of a gas turbine duct casing; a second gas turbine component that can be joined thereto, in particular a second wall segment (20) of a gas turbine duct casing, with a flange (21), which is particularly bent; and an eccentric clamping element (30), which is mounted rotatably about an axis of rotation (A) on the first gas turbine component and has an eccentric contour portion (31), whose radial distance (r) to the axis of rotation varies by an angle (φ) about the axis of rotation, in order to press the flange (21) of the second gas turbine component (20) against the first gas turbine component, in particular to clamp it between the first gas turbine component and the eccentric contour portion (31). | 02-04-2016 |
| 20160047276 | QUICK CHANGE INSERT - An insert for a component of a gas turbine is provided. The insert includes an insert portion and a retaining element such that the insert portion is retained by the retaining element so that movement of the insert portion relative to the retaining element is prevented. Additionally, a gas turbine component including the insert is provided as well as a method for inserting the insert into a gas turbine component. | 02-18-2016 |
| 20160102578 | SEAL RETAINING ASSEMBLY - A seal retaining assembly includes a first segment coupled to a first structure. Also included is a recess of the first segment, the recess defined by a first and second wall, the first wall defining a first wall aperture, the second wall defining a second wall aperture. Further included is a second segment having a tab disposed within the recess in fitted contact with the first and second wall to retain the second segment to the first segment in a radial direction, the tab defining a tab aperture, the first and second segment defining an axial gap therebetween, the first wall aperture, the second wall aperture and the tab aperture are aligned to form a passage. Yet further included is a flex seal within the axial gap. Also included is a pin in the passage to fix the second segment to the first segment in axial and circumferential directions. | 04-14-2016 |
| 20160123337 | VENTILATING FAN - A ventilating fan, includes a housing having an opening at a bottom surface thereof, a casing disposed in the housing, fan blades and a motor disposed in the casing, and a wiring box fixed on the casing and composed of a box body and a cover. The wiring box is fixed on the casing through a fixing structure, the fixing structure includes a first fixing means and a second fixing means, and the first fixing means includes a screw fixing structure, and the second fixing means includes an engaging fixing structure. An advantage of the ventilating fan lies in that, while preventing a user from detaching the wiring box manually, the ventilating fan has reduced components and can simplify operating steps during fixing the wiring box on the casing, and is thereby less time consuming. | 05-05-2016 |
| 20160160687 | OUTER DIFFUSER CASE FOR A GAS TURBINE ENGINE - An outer diffuser case of a diffuser case assembly for use in a gas turbine engine may have a housing orientated about an engine axis, a forward flange projecting radially outward from the housing, a mid-flange spaced axially aft of the forward flange and projecting radially inward from the housing, and an aft flange projecting radially outward from the housing. The mid flange is spaced axially between the forward and aft flanges and is configured to detachably engage an inner diffuser case of the case assembly. The forward flange is configured to detachably engage a high pressure compressor and the aft flange is configured to detachably engage a high pressure turbine of the engine. | 06-09-2016 |
| 20160160870 | AXIALLY SPLIT PUMP - An axially split pump for conveying a fluid has an axially split housing that includes a bottom part and a cover. The bottom part has a first sealing surface and the cover has a second sealing surface, the bottom part and the cover being fastened so that the two sealing surfaces have direct contact. A first sealing groove for the reception of a first string-like sealing element is in the sealing surfaces, and a second sealing groove is provided for the reception of a second string-like element, the second sealing groove being connected to the first sealing groove via an opening. A connection element is in the opening that has two lateral cut-outs respectively for the reception of a one of the string-like sealing elements. The cut-outs are arranged and configured so that the two string-like sealing elements run substantially in parallel in the region of the connection element. | 06-09-2016 |
| 20160160871 | AXIALLY SPLIT PUMP - An axially split pump for conveying a fluid includes an axially split housing with a bottom part and a cover. The bottom part has a first sealing surface and the cover has a second sealing surface. The bottom part and the cover are fastened to one another so that the two sealing surfaces are in direct contact with one another. At least one first sealing groove for the reception of a first sealing element is disposed in the sealing surfaces. A second sealing groove is disposed for the reception of a second sealing element. The first sealing groove and the second sealing groove are connected to one another through a connection region and an elastic pre-loading element is disposed in the connection region, which exerts a pre-load onto one of the two sealing elements. | 06-09-2016 |
| 20160160873 | AXIALLY SPLIT PUMP - An axially split pump for a fluid includes an axially split housing with a bottom and a cover, a rotatable shaft, and a side cover. The side cover has a first surface for cooperating with a second surface. The second surface extends over the bottom and the cover. The bottom has a first sealing surface and the cover has a second sealing surface. The bottom and the cover can be fastened so that the sealing surfaces are in direct contact. One sealing groove is in one of the sealing surfaces for the reception of a string-like sealing element, the sealing groove extending up to the second surface. A recess surrounding the shaft is in the second surface and a projection surrounding the shaft is in the first surface. The recess and the projection are arranged so that they form a ring-like groove for the reception of a ring-like sealing element. | 06-09-2016 |
| 20160160876 | COMPRESSING APPARATUS HOUSING AND COMPRESSING APPARATUS - There is provided a compressing apparatus housing including: an inner housing unit configured to house at least a portion of an impeller unit; an outer housing unit including an inner housing receiving unit configured to receive at least a portion of the inner housing unit; and an intermediate housing unit provided between the inner housing unit and the outer housing unit and configured to form a flow path together with at least one of the inner housing unit and the outer housing unit. | 06-09-2016 |
| 20160169247 | METHOD FOR THE POSITIONING OF A COVER DISK OF A PUMP AND PUMP | 06-16-2016 |
| 20160177765 | PINNED SEAL | 06-23-2016 |
| 20160177785 | JOINT ASSEMBLY AND A METHOD OF USING THE SAME | 06-23-2016 |
| 20160177787 | JOINT ASSEMBLY AND A METHOD OF USING THE SAME | 06-23-2016 |
| 20160201513 | TURBINE HOUSING FOR AN EXHAUST TURBOCHARGER | 07-14-2016 |
| 20170234163 | CONNECTION SYSTEM FOR HOUSING ELEMENTS OF A TURBINE INTERMEDIATE CASING | 08-17-2017 |
| 20220136409 | SPLIT CASE STRUCTURE FOR A GAS TURBINE ENGINE - An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a first wall, a second wall, a first case segment and a second case segment. The first wall extends axially along and circumferentially about an axial centerline. The second wall extends axially along and circumferentially about the axial centerline. The second wall is radially outboard of and axially overlaps the first wall. The first case segment is configured to form a first portion of the first wall and a first portion of the second wall. The second case segment is configured to form a second portion of the first wall and a second portion of the second wall. The second case segment is circumferentially adjacent and attached to the first case segment at a joint. | 05-05-2022 |
