Entries |
Document | Title | Date |
20080206048 | METHOD OF MANUFACTURING A GAS TURBINE CASING OUT OF COMPOSITE MATERIAL, AND A CASING AS OBTAINED THEREBY - A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness. | 08-28-2008 |
20080253883 | CASING - Casings are utilized within gas turbine engines in order to provide both an environmental containment for the engine core as well as inhibit release of debris should engine components fragment and fail in service. Traditionally, casings have taken the form of a solid containment shield to prevent debris and object release on percussive impingement with the casing. Such an approach avoids the uncertainties with respect to flap rupture propagation of the casing in use. However such casings are relatively thick and therefore provided a severe weight penalty in aircraft. By providing a casing which has a relatively thinner containment shield and an additional, where required, catch layer rupture of the containment shield can be allowed whilst the catch layer prevents rupture propagation and therefore aperture development to a sufficient size to allow the debris to pass completely through the casing at all or with sufficient energy to cause damage. | 10-16-2008 |
20080304959 | Joint Between a Metal Part and a Ceramic Part Based Sic and/or C - An assembly between a metal piece and a ceramic material piece made of SiC and/or C based ceramic material. The assembly includes a stack structure including the following elements assembled together in pairs in this order, by brazing: the metal piece; a first intermediate piece; a second intermediate piece; and the ceramic material piece. The second intermediate piece is made of another ceramic material, that is chemically less reactive relative to metals than are SiC or C, and that presents a coefficient of expansion smaller than that of the material constituting the metal piece. The first intermediate piece is made of metal and can deform to compensate for expansion difference between the metal piece and the second intermediate piece. The assembly can be used in a turbomachine. | 12-11-2008 |
20080304960 | PLASTIC COMPRESSOR HOUSING AND METHOD FOR PRODUCING A PLASTIC COMPRESSOR HOUSING - A plastic compressor housing, in particular a radial compressor housing, preferably for a turbocharger, includes at least one first housing part and at least one second housing part, which respectively comprise at least in some areas at least one thermoset material. The first housing part and/or the second housing part comprises or comprise at least two individual elements, wherein the first housing part and the second housing part are coated at least in some areas with at least one thermoset body or at least one thermoplastic body such that the first housing part, the second housing part and the individual elements of the first housing part and/or the second housing part respectively are in contact at least in some areas with the thermoset body or the thermoplastic body. Also disclosed is a method for producing a plastic compressor housing and a turbocharger. | 12-11-2008 |
20080310956 | VARIABLE GEOMETRY GAS TURBINE ENGINE NACELLE ASSEMBLY WITH NANOELECTROMECHANICAL SYSTEM - A nacelle assembly includes an inlet lip section and a cowl section downstream of the inlet lip section. At least a portion of the cowl section is flexed to take various shapes through a nanoelectromechanical system and thereby influence an effective boundary layer thickness of the nacelle assembly. | 12-18-2008 |
20080317589 | Compressor Housing for Use at Low Temperatures - The invention relates to a turbo machine comprising a housing. Said turbo machine is designed especially as a turbo compressor for use at low temperatures, the housing preferably being made of a cold-resistant material that has a martensitic structure. | 12-25-2008 |
20090028697 | LOW TRANSIENT THERMAL STRESS TURBINE ENGINE COMPONENTS - A turbine vane includes a platform; and at least one airfoil mounted to the platform and having a trailing edge and a leading edge, wherein the vane is composed of a functionally graded material having a first material and a second material, wherein the trailing edge includes a greater amount of the first material than the second material, and the leading edge includes a greater amount of the second material than the first material. | 01-29-2009 |
20090035131 | Component for a gas turbine engine - Blades for gas turbine engines which are formed from composite materials have problems with respect of resistance to impacts such as bird strikes. Previous blades formed from metals had some ductility towards the trailing edge which could accommodate the whiplash effects of impacts. With regard to composite materials such ductility is not present. By providing projections | 02-05-2009 |
20090041579 | Torque converter having stator with cast-in side plate - A method for manufacturing a torque converter includes providing an outer race of a one way clutch, contacting the outer race with a side plate, and casting a stator housing together with the outer race and the side plate. A torque converter is also provided. | 02-12-2009 |
20090053050 | GAS TURBINE SHROUD SUPPORT APPARATUS - A support apparatus for a gas turbine shroud is disclosed. The apparatus includes an outer shroud block having a coupling connectable to a casing of the gas turbine and a shroud component having a forward flange and an aft flange. The shroud component is attached to the outer shroud block via the forward flange and the aft flange. The apparatus further includes a damper disposed between the outer shroud block and the shroud component and a biasing element disposed within the outer shroud block. A translational degree of freedom between the damper and the outer shroud block defines a direction of motion of the damper. The biasing element is in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper. | 02-26-2009 |
20090053051 | PLASTIC COMPRESSOR HOUSING AND METHOD FOR PRODUCING SAME - A plastic compressor housing, in particular a radial flow compressor housing, preferably for a turbocharger, has at least one thermosetting plastic body for providing an intake pipe, a compressor duct, and an outlet pipe, and a thermoplastic at least partially covering the thermosetting plastic body in a hood-like fashion. The thermosetting plastic body is formed as a basic body and the thermoplastic is injection molded on the basic body. At least a first anchoring element is embodied on at least a first surface of the thermosetting plastic body and at least a second surface of the first anchoring element is substantially completely covered with the thermoplastic. The disclosure further relates to a method for producing a plastic compressor housing. | 02-26-2009 |
20090060728 | PUMPS AND PUMP-HEADS COMPRISING INTERNAL PRESSURE-ABSORBING MEMBER - An exemplary pump includes a pump housing defining a pump cavity, a movable pumping member situated in the pump cavity, and at least one pressure-absorbing member located inside the pump housing. The housing also has an inlet and an outlet, and includes at least one interior non-wearing location that contacts liquid in the pump housing when the pump housing is primed with the liquid. The movable pumping member, when driven to move, urges flow of the liquid from the inlet through the pump cavity to the outlet. The at least one pressure-absorbing member is located inside the pump housing at the non-wearing location and contacts the liquid. The pressure-absorbing member has a compliant property to exhibit a volumetric compression when subjected to a pressure increase in the liquid contacting the pressure-absorbing member, the volumetric compression being sufficient to alleviate at least a portion of the pressure increase. | 03-05-2009 |
20090068004 | BRAZED JOINT BETWEEN A TITANIUM-BASED METAL PART AND A CERAMIC PART BASED ON SILICON CARBIDE (SIC) AND/OR CARBON - The assembly comprises a stack structure made up of the following elements assembled together in pairs by brazing: the titanium-based metal piece ( | 03-12-2009 |
20090074570 | Local application of a protective coating on a shrouded gas turbine engine component - A gas turbine engine component includes a blade section having an inner end and an outer end, a shroud section at the outer end, and a platform at the inner end. A protective coating is disposed on the shroud, where the blade section is substantially free of the protective coating. The protective coating may also be disposed on the platform. | 03-19-2009 |
20090081032 | COMPOSITE AIRFOIL - A turbine component includes mounting structure for attaching the turbine component. A core is attached to the mounting structure. The core is made from a structural material. A plastic airfoil portion envelopes at least a portion of the core. | 03-26-2009 |
20090081033 | Stacked Lamellae Ceramic Gas Turbine Ring Segment Component - A gas turbine ring segment ( | 03-26-2009 |
20090081034 | Oilfield Equipment Composed of a Base Material Reinforced With a Composite Material - Oilfield equipment is provided that includes a base material less subject to abrasion, corrosion, erosion and/or wet fatigue than conventional oilfield equipment materials such as carbon steel, and a reinforcing composite material for adding stress resistance and reduced weight to the oilfield equipment. | 03-26-2009 |
20090087309 | Protective ring for the fan casing of a gas-turbine engine - A protective ring ( | 04-02-2009 |
20090104030 | ASSEMBLY - An assembly includes a first member and a second member, the first member including a first material composition and the second member including a second material composition. The first and second material compositions each include one or more isotopes of the same element, which are arranged to permit distinguishing between the first and second members or 0 parts thereof. | 04-23-2009 |
20090142190 | Frame structure for fan - The present invention relates to a fan frame structure including a plastic frame and a metal fixing frame, in which at least two support arms are disposed on the rim of the fixing frame and extended outwardly therefrom, the outwardly extended distance of each support arm shall be beyond the range of an accommodation space of the frame, the portion of the support arm beyond the accommodation space in integrally enclosed by the plastic material of the frame. Therefore, the present invention not only significantly lowers the material cost, but also produces a variety of products in coordination with various specifications of fixing frame by using a single injection mold for the frame to save the mold cost. | 06-04-2009 |
20090148281 | Resinous shroud and manufacturing method of the same - A resinous shroud includes a resinous wall portion formed between a portion corresponding to a casing and a portion corresponding to a retaining member in a shroud portion when a resin material is filled from a gate portion. Thereby, a flow of the resin material to the portion corresponding to the casing from a portion corresponding to the gate portion can be dispersed by the resinous wall portion. Alternatively, an extended resinous wall portion may be formed in place of the resinous wall portion. Therefore, welds generated at the casing can be made small, and cambers generated at the casing can be suppressed. | 06-11-2009 |
20090155065 | COMPOSITE CONTAINMENT CASINGS - Composite containment casing including a body having an interior, an abradable system integrally joined to the interior of the body of the containment casing wherein the abradable system comprises, a sandwich structure including a first facesheet and a second facesheet position about at least one core layer, and at least one abradable layer applied to the sandwich structure wherein the at least one core layer comprises any of a cell configuration, a columnar configuration, or a truss configuration and wherein the sandwich structure is strong radially and weak circumferentially. | 06-18-2009 |
20090162194 | Annular component - A stator vane assembly for a compressor has a support structure which carries and is bounded by an annular stator vane structure. The stator vane structure comprises a central bore and a sleeve carried on the central bore. The sleeve is disposed between the support structure and bore of the annular stator vane structure. The annular stator vane structure is made from a non-metallic composite material and the sleeve is made from a first material. The coefficient of thermal expansion of the non metallic material is equal to or less than the co-efficient of thermal expansion of the first material. | 06-25-2009 |
20090169372 | METHOD OF PRODUCING A PROTECTIVE COATING, PROTECTIVE COATING, AND COMPONENT WITH A PROTECTIVE COATING - A method for producing a wear-resistant, temperature-resistant, and corrosion-resistant protective coating for a component, in particular for components of a gas turbine, using thermal spraying, wherein during the application onto the component of the protective coating, which consists of a hard material-metal combination, in order to produce an abrasive surface a structuring of that surface of the protective coating that faces away from the component takes place, the hard material or materials consisting of boron nitride particles, titanium carbide particles, tungsten carbide particles, chromium carbide particles, and zirconium oxide particles, or a mixture thereof, and the hard materials having a particle size of 0.1 μm-200 μm, and the protective coating having a thickness of 10 μm-6.0 mm. | 07-02-2009 |
20090232647 | AIRFOIL ASSEMBLY AND METHOD OF FORMING SAME - An airfoil or vane for a combustive power plant includes an inner core formed from a first composite material having discontinuous fibers. An outer sleeve is formed from a second composite material having continuous fibers. The first composite material is different from the second composite material. The outer sleeve generally surrounds and is bonded or otherwise connected to the inner core. A method of fabrication includes injecting or otherwise introducing thermoplastic fiber composite material including chopped or otherwise discontinuous fibers into a mold to form the core and platforms of an airfoil assembly. The injected thermoplastic fiber composite material is then cured in the mold. The cured thermoplastic fiber composite material is then removed from the mold. A layup including one or more surface plies of a thermoset continuous fiber composite material is then applied to the core material. The surface plies are then compressed and cured in a mold. | 09-17-2009 |
20090246008 | Layer System - Thermal barrier coating layer systems, in addition to good thermal barrier properties, also have to have a long service life of the thermal barrier coating. The layer system according to the invention comprises a specially adapted layer sequence of metallic bonding layer, inner ceramic layer and outer ceramic layer. | 10-01-2009 |
20090257863 | Turbine assembly - The ‘hydrokinetic turbine assembly’ is a device for the conversion of the kinetic energy of oscillating tidal currents into rotary torque to generate clean electric power. This device is a horizontal axis hydroturbine with a plurality of trapezoidal symmetrical blades placed at about 45 degrees to the axis. The inclination of the blades assures its maximum energy conversion capacity and the dual reaction function of the turbine where ‘floods and ebbs” are alternatively converted into rotary torque. The inner blade frame, its aerodynamic contour, and at least one connective circumferential blade-ring, add strength buoyancy and sensitivity to slow currents. This hydrokinetic turbine is separated from the electric generators and can be placed in pre-planned current flow locations for greater efficiency. | 10-15-2009 |
20090257864 | Hydraulic machine member with an abrasion-resistant reinforced edge and a hydraulic machine using this member - This hydraulic machine member has at least one flow of water passing through it, and comprises at least one wetted surface extending between two edges of the member, at least one of the edges of the member and part of the adjacent wetted surface being reinforced and formed by at least one removable solid element made from material having a high resistance to abrasion. | 10-15-2009 |
20090257865 | NI-BASE ALLOY FOR TURBINE ROTOR OF STEAM TURBINE AND TURBINE ROTOR OF STEAM TURBINE - An Ni-base alloy for a turbine rotor of a steam turbine contains in percent by weight C: 0.05 to 0.15, Cr: 22 to 28, Co: 10 to 22, Mo: 8 to 12, Al: 0.8 to less than 1.5, Ti: 0.1 to 0.6, B: 0.001 to 0.006, Re: 0.1 to 2.5, and the balance of Ni and unavoidable impurities. | 10-15-2009 |
20090263239 | Ring structure with a metal design having a run-in lining - A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt. | 10-22-2009 |
20090269193 | MULTI-CAST TURBINE AIRFOILS AND METHOD FOR MAKING SAME - A gas turbine engine airfoil is made from separate cast sections having different cast alloy structures. The cast alloy structures are selected on the basis of the local operating conditions of each section. Friction welding can be used to join the sections together. | 10-29-2009 |
20090290978 | TURBINE ENGINE FOR AIRCRAFT - According to the invention, the internal wall (5.1) of the air intake (2) and the housing (12.1) for the fan (3) are pieces of composite fibre/resin material, overlap-jointed at the ends thereof (5.1R) and (12.1A). | 11-26-2009 |
20090290979 | COMPRESSOR HOUSING - The present invention provides a compressor housing capable of reducing the weight of a compressor without leading to an increase in the size and a reduction in the efficiency of the compressor. The compressor housing includes: an inner cylinder made of a plastic material and extending in an axial direction and in a circumferential direction to surround blade tips of the blades; and an outer cylinder made of a plastic material and extending in the axial direction and in the circumferential direction to surround the inner cylinder. The inner cylinder and the outer cylinder are bonded or jointed at the first end, opposite the second end where the volute is formed. | 11-26-2009 |
20090304500 | TURBOCHARGER HOUSING WITH A CONVERSION COATING AND METHODS OF MAKING THE CONVERSION COATING - A turbocharger includes a center housing having a bearing surface configured to contact an inner surface of a unison ring. A conversion coating is impregnated onto at least the bearing surface of the center housing. | 12-10-2009 |
20090317246 | Guide Vane Arrangement for a Driving Mechanism - The invention relates to a guide-vane arrangement ( | 12-24-2009 |
20090324401 | ARTICLE HAVING A PROTECTIVE COATING AND METHODS - The article comprises a substrate having a first surface, a plurality of elements extending from the first surface, and a protective coating disposed between at least a portion of the plurality of elements, on at least a portion of the plurality of elements, or both. The plurality of elements are integral with the substrate. A method for applying a protective coating onto an article is also provided. | 12-31-2009 |
20100008771 | PUMP UNIT - A pump assembly has a housing formed of at least two metallic housing parts ( | 01-14-2010 |
20100014964 | ELECTRO-FORMED SHEATH FOR USE ON AIRFOIL COMPONENTS - An article for protecting an airfoil component includes a sheath having an outer side and an inner side that forms a cavity for receiving a leading edge of the airfoil component. The sheath is made of cobalt and phosphorous to protect the leading edge of the airfoil component from erosion. | 01-21-2010 |
20100021290 | Ceramic matrix composite turbine engine vane - A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The shell includes a region having a coefficient of thermal expansion (CTE) varying with depth. | 01-28-2010 |
20100028142 | Turbocharger - To provide a turbocharger whose lifetime is long, which is capable of inexpensively and precisely performing nozzle vane angle synchronous control by using inexpensive and highly wear resistant components in a link mechanism for driving a rotation mechanism of nozzle vanes of an adjustable nozzle mechanism. As pins fixedly arrayed in a ring plate rotatably supported on the turbocharger, that set an angle of the nozzle vanes for controlling an amount of exhaust gas for rotating a turbine rotor, each pin in which a hard coating with a thickness of approximately 2 μm which is formed of Al, Cr, Si, and N by physical vapor deposition is formed onto an austenitic stainless steel as a base material, is used. | 02-04-2010 |
20100054932 | Circumferential Shroud Inserts for a Gas Turbine Vane Platform - Protective insert plates ( | 03-04-2010 |
20100054933 | STATIONARY TURBINE COMPONENT WITH LAMINATED SKIN - A stationary turbine engine component, such as a turbine vane, includes a internal spar and an external skin. The internal spar is made of a plurality of spar laminates, and the external skin is made of a plurality of skin laminates. The plurality of skin laminates interlockingly engage the plurality of spar laminates such that the external skin is located and held in place. This arrangement allows alternative high temperature materials to be used on turbine engine components in areas where their properties are needed without having to make the entire component out of such material. Thus, the manufacturing difficulties associated with making an entire component of such a material and the attendant high costs are avoided. The skin laminates can be made of advanced generation single crystal superalloys, intermetallics and refractory alloys. | 03-04-2010 |
20100061846 | REPAIRED TURBINE EXHAUST STRUT HEAT SHIELD VANES AND REPAIR METHODS - A method of repairing a turbine exhaust case strut heat shield vane includes removing a damaged portion of the vane, solution heat treating the vane, attaching a replacement section to the vane, and relieving local stresses in an attachment area between the replacement section and the vane. | 03-11-2010 |
20100061847 | STEAM TURBINE PART INCLUDING CERAMIC MATRIX COMPOSITE (CMC) - A steam turbine part includes a ceramic matrix composite (CMC). The part may be made wholly or partially of CMC. The CMC eliminates the possibility of oxidation and thus increases steam turbine availability and reliability | 03-11-2010 |
20100074740 | VANE RING, AND METHOD FOR THE PRODUCTION THEREOF - The invention relates to a vane ring of a turbo engine, particularly a gas turbine, comprising a vane support ring and several guide vanes that are mounted on the vane support ring. According to the invention, the vane support ring and the guide vanes are made of different materials, the materials of which the guide vanes are made being of a higher quality than the material of which the vane support ring is made. | 03-25-2010 |
20100074741 | HIGHLY CORROSION-RESISTANT FIXED BLADE ASSEMBLY FOR A STEAM TURBINE, IN PARTICULAR A GEOTHERMAL IMPULSE TURBINE - A highly corrosion-resistant fixed blade assembly ( | 03-25-2010 |
20100086397 | Surface Treatments for Turbine Components to Reduce Particle Accumulation During Use Thereof - A turbine engine component includes at least one treated surface wherein the treated surface has a surface roughness (Ra) of less than 12 microinches; and a hard coating disposed on the superfinished surface, wherein the hard coating is a nitride and/or a carbide material at a thickness of less than 50 microns formed using electron beam physical vapor deposition, cathodic arc evaporation, or magnetron sputtering. disclosed are methods for substantially preventing micropitting on a surface of a turbine engine component. | 04-08-2010 |
20100086398 | METHOD FOR COATING SLIDING SURFACE OF HIGH-TEMPERATURE MEMBER, HIGH-TEMPERATURE MEMBER AND ELECTRODE FOR ELECTRO-DISCHARGE SURFACE TREATMENT - A sliding surface of a high-temperature portion is subjected to an electro-discharge surface treatment with one or both of a high-temperature hard material (4) and a material having a lubricating property at a high temperature (6). The high-temperature hard material (4) is any or a mixture of cBN, TiC, TiN, TiAlN, TiB | 04-08-2010 |
20100092281 | TURBINE RING ASSEMBLY FOR GAS TURBINE - A turbine ring assembly for a gas turbine comprises a one-piece split ring ( | 04-15-2010 |
20100104433 | CERAMIC SHROUD ASSEMBLY - A ceramic shroud assembly suitable for use in a gas turbine engine comprises a metal clamp ring shrink fitted around a ceramic shroud ring and an insulating and compliant interlayer. The interlayer is positioned between the metal clamp ring and the ceramic shroud ring. | 04-29-2010 |
20100111685 | GAS TURBINE ENGINE COMPONENT, A TURBOJET ENGINE PROVIDED THEREWITH, AND AN AIRCRAFT PROVIDED THEREWITH - A gas turbine engine component is provided including at least one ring element, and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. The load carrying vanes have an internal structure with an anisotropic load carrying property, and the internal structure is configured so that a main load carrying direction is in parallel with the extension direction of the load carrying vane. The component includes a stiffening structure bridging the distance between at least two adjacent load carrying vanes in the circumferential direction of the ring element, and the at least two adjacent load carrying vanes are attached to the stiffening structure. | 05-06-2010 |
20100124492 | TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME - Turbine nozzles and methods of manufacturing the turbine nozzles are provided. In an embodiment, by way of example only, a turbine nozzle includes a first ring, a vane, and a first joint. The first ring comprises a single unitary component and having a first opening and including a first metal alloy. The vane includes a first end disposed in the first opening and includes a second metal alloy. The first joint is formed in the first opening between the first ring and the vane and includes a first braze layer and an oxide layer. The first braze layer is disposed adjacent to the oxide layer, and the first braze layer and the oxide layer are disposed between the first ring and the vane. | 05-20-2010 |
20100143108 | Device for the Protection of Components Having A Flammable Titanium Alloy From Titanium Fire, and Method for the Production Thereof - The use of titanium-based materials in the manufacturing of gas turbines, especially of engines, and, in particular, of compressors is made possible in that a device is devised that protects the components (guide vanes, guide vane stages, rotor blades, rotor blade stages) that are subject to the action of titanium fire and/or FODs by employing a layer system that includes at least two layers, is situated on the surface of the components to be protected, and is bonded thereto, as the case may be, via an adhesion-promoting layer is disclosed. The outermost layer is ceramic; the layer that is subjacent thereto is of metallic nature. Additional layers can optionally follow, ceramic and metallic layers alternating with one another. Moreover, a method is provided for producing the device. Through the at least partial use of titanium alloys, in particular for guide vanes of gas turbines, the weight of compressors can be significantly reduced in that the need for the nickel- or steel-based structural materials used under the related art is eliminated in favor of lighter titanium alloys. | 06-10-2010 |
20100150706 | ARTICLES MADE FROM COMPOSITE MATERIALS HAVING TOUGHENED AND UNTOUGHENED REGIONS - Articles having a body including a composite material having at least one toughened region and at least one untoughened region, the toughened region containing a toughening agent selected from the group consisting of polymers, nano fibers, nano particles, and combinations thereof where the toughened region includes a toughened resin having a fracture toughness of at least about 1.0 MPa-m | 06-17-2010 |
20100150707 | Airfoil - An airfoil has a hollow shell providing external airfoil surfaces, and a corrugated core within the shell. The core contacts inner surfaces of the shell to support the shell. The airfoil is formed by consolidating a hollow shell pre-form and a corrugated core pre-form. At least a part of the hollow shell has a leading edge shell portion and/or a trailing edge shell portion which, before consolidation of the pre-forms, is a unitary body having a shape which wraps around the respective edge. | 06-17-2010 |
20100150708 | Segmented Composite Inner Ferrule and Segment of Diffuser of Axial Compressor - A ferrule of a stator with blades of an axial turbomachine consists of at least two segments having the general form of an arc of a circle and intended to be arranged end to end, so as to form the ferrule, where each segment contains on its outside a plurality of openings arranged at regular distances along the general arc of the circle of the segment, into each of which fits the end of a blade of the stator. Each end of a segment possesses a section of which the profile essentially corresponds with that of the end of the corresponding blade when the segment is placed on the blades of the stator, such that the joint between two adjacent segments corresponds with the profile of the corresponding blade. | 06-17-2010 |
20100158680 | CMAS MITIGATION COMPOSITIONS, ENVIRONMENTAL BARRIER COATINGS COMPRISING THE SAME, AND CERAMIC COMPONENTS COMPRISING THE SAME - Calcium magnesium aluminosilicate (CMAS) mitigation compositions selected from rare earth elements, rare earth oxides, zirconia, hafnia partially or fully stabilized with alkaline earth or rare earth elements, zirconia partially or fully stabilized with alkaline earth or rare earth elements, magnesium oxide, cordierite, aluminum phosphate, magnesium silicate, and combinations thereof when the CMAS mitigation composition is included as a separate CMAS mitigation layer in an environmental barrier coating for a high temperature substrate component. | 06-24-2010 |
20100158681 | NI-BASED ALLOY FOR A FORGED PART OF A STEAM TURBINE WITH EXCELLENT HIGH TEMPERATURE STRENGTH, FORGEABILITY AND WELDABILITY, ROTOR BLADE OF A STEAM TURBINE, STATOR BLADE OF A STEAM TURBINE, SCREW MEMBER FOR A STEAM TURBINE, AND PIPE FOR A STEAM TURBINE - A Ni-based alloy for a forged part of a steam turbine having excellent high temperature strength, forgeability and weldability includes, in percentage by mass, 0.01 to 0.15 of C, 18 to 28 of Cr, 10 to 15 of Co, 8 to 12 of Mo, 1.5 to 2 of Al, 0.1 to 3 of Ti, 0.001 to 0.006 of B, 0.1 to 0.7 of Ta, and the balance of Ni plus unavoidable impurities. | 06-24-2010 |
20100158682 | NI-BASED ALLOY FOR A CASTING PART OF A STEAM TURBINE WITH EXCELLENT HIGH TEMPERATURE STRENGTH, CASTABILITY AND WELDABILITY, TURBINE CASING OF A STEAM TURBINE,VALVE CASING OF A STEAM TURBINE, NOZZLE BOX OF A STEAM TURBINE, AND PIPE OF A STEAM TURBINE - A Ni-based alloy for a casting part of a steam turbine having excellent high temperature strength, castability and weldability includes, in percentage by mass, 0.01 to 0.15 of C, 18 to 28 of Cr, 10 to 15 of Co, 8 to 12 of Mo, 1.5 to 2 of Al, 0.1 to 3 of Ti, 0.001 to 0.006 of B, 0.1 to 0.7 of Ta, and the balance of Ni plus unavoidable impurities. | 06-24-2010 |
20100166547 | WIND TURBINE WITH REDUCED RADAR SIGNATURE - Various components of a shrouded wind turbine are coated with a radar absorbent material. The resulting wind turbine has a reduced radar signature compared to conventional wind turbines. | 07-01-2010 |
20100166548 | STEAM TURBINE BLADE AND METHOD FOR MANUFACTURING THE SAME - A steam turbine blade includes a coating film formed at least a portion of a surface of the steam turbine blade, the coating film containing a ceramic matrix and nanosheet particles dispersed in the ceramic matrix. The steam turbine blade is employed as one of stator blades or one of rotor blades in a steam turbine. The steam turbine includes a turbine rotor, the rotor blades implanted in the turbine rotor, the stator blades provided in an upstream side of the corresponding rotor blades, and a turbine casing supporting the stator blades and accommodating turbine rotor, the rotor blades and the stator blades. The steam turbine is also configured such that the rotor blades are paired with the corresponding stator blades to form turbine stages arranged in an axial direction of the turbine rotor, thereby forming steam paths. | 07-01-2010 |
20100189555 | METHOD AND ASSEMBLY FOR GAS TURBINE ENGINE AIRFOILS WITH PROTECTIVE COATING - A method of processing turbine airfoils includes depositing a protective coating on first and second turbine airfoils, and bonding the first and second turbine airfoils together after the deposition such that there is an open throat between the first and second turbine airfoil and at least portions of surfaces in the open throat are coated with the protective coating. | 07-29-2010 |
20100189556 | SEGMENTED CERAMIC MATRIX COMPOSITE TURBINE AIRFOIL COMPONENT - A segmented component for use with a gas turbine engine comprises a radially extending gas path portion. The gas path portion is for interacting with gas flow from the gas turbine engine. The component is divided into axially aligned segments comprising a forward segment, an aft segment, and a plurality of middle segments disposed between the forward segment and the aft segment. The middle segments comprise radially elongate ceramic matrix composite material plates. In one embodiment, the gas path portion comprises an airfoil for a turbine blade. In another embodiment, the gas path portion comprises a removable platform for a turbine blade. In another embodiment, the gas path portion comprises an airfoil for a turbine vane. | 07-29-2010 |
20100202876 | STEAM TURBINE FACILITY - Provided is a steam turbine facility capable of suppressing the possibility of vibration occurrence and a drastic increase in facility cost, thereby realizing an increase in size of the facility, even if steam conditions of 650° C. or higher are adopted. In a steam turbine facility including a high-pressure turbine, an intermediate-pressure turbine, and a low-pressure turbine, the intermediate-pressure turbine is separated into a first intermediate-pressure turbine on a high-temperature and high-pressure side and a second intermediate-pressure turbine on a low-temperature and low-temperature side, at least any one of the rotors and casings of the steam-introduction-side turbines into which steam with a temperature of 650° C. or higher is introduced is formed from Ni-based alloy, and at least any one of the overall rotors and the overall casings of the turbines are constructed by joining together a plurality of rotor members or casing members by welding. | 08-12-2010 |
20100209235 | METHOD AND APPARATUS FOR A STRUCTURAL OUTLET GUIDE VANE - In one aspect, a method for assembling an outlet guide vane is provided. The method includes providing an outlet guide vane frame having a first side and a second side. The outlet guide vane includes a radially inward flange coupled to a radially outward flange by a leading edge. A trailing edge is coupled to the radially inward flange and the radially outward flange aft of the leading edge. A cavity is defined between the radially inward flange, the radially outward flange, the leading edge, and the trailing edge. A first and a second mating surface circumscribe the cavity on the first and second sides respectively. The method further includes coupling a filler portion within the cavity wherein the filler portion includes a third side and a fourth side, coupling a first skin to the third side and the first mating surface, and coupling a second skin to the fourth side and the second mating surface, wherein at least one of the first skin and the second skin are fabricated from a composite material. | 08-19-2010 |
20100247303 | DUCT MEMBER BASED NOZZLE FOR TURBINE - A nozzle for a turbine includes a duct member having a substantially uniform wall thickness. Nozzles made of different materials can be used. | 09-30-2010 |
20100266396 | RISER CLAMP FOR PUMPS FOR PUMPING MOLTEN METAL - This disclosure features a transfer pump for pumping molten metal having a riser with a reusable socket. The pump includes a motor, support structure above a molten metal bath, a motor driven shaft and an impeller on an end of the shaft rotatable in a base. A riser made of refractory material extends from a transfer opening in the base to the support structure. The riser has a passageway for molten metal along a length of the riser. A clamp has a first clamp portion fixedly connected to the support structure and a second clamp portion that is pivotable with respect to the first clamp portion. A fastener is used to open and close the clamp. Sections of a split socket each have a flange and a body portion. The socket is received in the clamp such that the flanges of the socket are disposed above the clamp, and when the clamp is closed the socket holds the riser. | 10-21-2010 |
20100310362 | Housing for a Blade Wheel - A turbine housing for a turbine wheel of an exhaust gas turbocharger, is formed from a casting material and comprises at least two flow chambers that are separated from each other by a flow separator. The flow separator is embodied as a separate insert especially as a sheet metal part or a cast part, that is embedded into a wall region of the housing. | 12-09-2010 |
20100322760 | Interlocked CMC Airfoil - A ceramic matrix composite (CMC) airfoil assembled from a pressure side wall ( | 12-23-2010 |
20110002779 | Method for Manufacturing by Molding a Machine Structural Element Having an Abradable Surface, and Structural Element - A method for manufacturing a machine structural element from a molded composite material includes manufacturing of an abradable layer made integrally from the material of the element. The method consists in adding a filler material to the resin at the surface to be made abradable, the filler material being able to disintegrate, such as e.g. transitioning to vapor phase, during the heat treatment of polymerizing the resin in order to create porosity inside the layer. The porosity thus created provides the relevant surface with properties of abradability. | 01-06-2011 |
20110008156 | COMPOSITE TURBINE NOZZLE - A composite nozzle segment includes one or more airfoils extending radially between arcuate radially outer and inner band segments having band plies curved about a centerline axis, an outer chordal seal line on an outer aft flange of the outer band segment, and thickened areas in corners of the outer aft flange along pressure and suction side edges of the outer band segment. The thickened areas may be thickest at the pressure and suction side edges and thinnest near a middle of the outer band segment. The thickened areas taper off from an aft end of the thickened area towards a forward flange of the outer band segment. Insert plies may be disposed between some of the band plies within the thickened areas may be grouped together in a discrete group or be interspersed with some of the band plies. The insert plies may have triangular shapes. | 01-13-2011 |
20110008157 | TURBINE STATOR AIRFOILS WITH INDIVIDUAL ORIENTATIONS - In accordance with an exemplary embodiment, a turbine stator component includes a first endwall; a second endwall; a first stator airfoil coupled between the first and second endwalls; and a second stator airfoil adjacent to the first airfoil and coupled between the first and second endwalls. The first stator airfoil has first crystallographic primary and secondary orientations. The second stator airfoil has second crystallographic primary and secondary orientations, the first crystallographic primary and secondary orientations being different from the second crystallographic primary and secondary orientations. | 01-13-2011 |
20110008158 | COOLED HOUSING CONSISTING OF A TURBINE HOUSING AND A BEARING HOUSING FOR A TURBOCHARGER - A housing of a turbo charger has a turbine housing and a bearing housing. A cooling jacket is formed of at least one or more shell elements that are fixed to the outside of the housing and that form therewith a cavity into which a coolant can be introduced. | 01-13-2011 |
20110014038 | WIND TURBINE WITH SKELETON-AND-SKIN STRUCTURE - A wind turbine comprises a turbine shroud and optionally an ejector shroud. The turbine shroud and/or the ejector shroud include a skeleton support structure, with a skin covering at least a portion of the turbine shroud and/or ejector shroud skeleton. In other embodiments, leading and trailing edges of the turbine shroud and/or ejector shroud are made of a rigid material and are not covered by the skin of the shroud. | 01-20-2011 |
20110038722 | FLUID INTAKE ASSEMBLY - A fluid intake assembly adapted for use with a turbo-machine is provided. The fluid intake assembly provides an efficient fluid inlet assembly including a casing adapted to guide fluid into the turbo-machine. The casing includes an inner wall, the inner wall having a lining of a resin infused composite material. A method of producing a fluid intake assembly for use with a turbo-machine is also provided. | 02-17-2011 |
20110038723 | TURBINE HOUSING WITH WALL CLADDING - A turbine housing for a turbine is provided. The turbine housing includes a wall cladding on an inner wall of the turbine housing. In a region of joint flanges, the wall cladding is arranged and embodied such that the wall cladding reduces convective heat transfer and thermal radiation in a region of the joint flanges. | 02-17-2011 |
20110052382 | COMPOSITE CASING FOR ROTATING BLADES - A gas turbine engine includes a fan including a plurality of circumferentially spaced rotatable blades, and a fan casing for containing fragments of fan blades in the event of blade release, the fan casing having a shell surrounding the blades and circumscribing a containment zone of the fan. The shell is made of a fiber reinforced polymer composite material which includes nanoparticles. | 03-03-2011 |
20110052383 | COMPOSITE FAN CONTAINMENT CASE - A gas turbine engine fan section includes first and second composite layers providing a generally cylindrical case. Axially spaced apart rings are arranged between the first and second composite layers and form reinforcing ribs that provide a fan containment area axially between the rings. A belt is arranged over and spans the fan containment area between the reinforcing ribs. A fan blade has a tip in proximity to the first composite layer without any intervening structural support between the tip and the first composite layer, which provides a fan blade rub resistant surface. A method of manufacturing a fan containment case includes wrapping at least one first composite layer around a mandrel. Axially spaced apart rings are arranged circumferentially about the first composite layer. At least one second composite layer is wrapped around the rings and first composite layer to provide reinforcing ribs at the rings. | 03-03-2011 |
20110052384 | CERAMIC TURBINE SHROUD SUPPORT - A turbine shroud includes a ceramic shroud ring configured to surround a plurality of turbine rotor blades, a plurality of slots circumferentially distributed around the ceramic shroud ring, a forward metallic support ring, a plurality of tabs attached to a forward edge of the forward metallic support ring configured to engage a turbine support case, and a plurality of tabs attached to an aft edge of the forward metallic support ring received by the slots of the ceramic shroud ring. Only two axially extending radial surfaces of each of the tabs attached to the aft edge of the forward metallic support ring are configured to contact the slots of the ceramic shroud ring. | 03-03-2011 |
20110064569 | NICKEL-BASE ALLOY FOR FORGING OR ROLLING AND STEAM TURBINE COMPONENT MADE OF THE SAME - In one embodiment, a nickel-base alloy for forging or rolling contains, in weight %, carbon (C): 0.05 to 0.2, silicon (Si) 0.01 to 1, manganese (Mn): 0.01 to 1, cobalt (Co): 5 to 20, iron (Fe): 0.01 to 10, chromium (Cr): 15 to 25, and one kind or two kinds or more of molybdenum (Mo), tungsten (W) and rhenium (Re), with Mo+(W+Re)/2: 8 to 25, the balance being nickel (Ni) and unavoidable impurities. | 03-17-2011 |
20110076140 | HOUSING FOR THE NACELLE OF A WIND TURBINE - Disclosed is a housing for the nacelle of a wind turbine, comprising a support structure ( | 03-31-2011 |
20110081238 | GAS TURBINE ENGINE SHEET METAL VANE - A gas turbine engine stator vane has a sheet metal body with a pressure surface and a suction surface extending chordwise from a leading edge to a trailing edge. The sheet metal body has opposed pressure and suction side trailing end portions that meet at a joint upstream from the trailing edge of the airfoil. The pressure and suction surfaces of the sheet metal body are parallel to one another between the joint and the trailing edge, thereby forming a straight non-tapering trailing edge section from the joint to the trailing edge of the airfoil. | 04-07-2011 |
20110097201 | STEAM TURBINE CASING SYSTEM - The disclosure relates to a steam turbine outer casing that can be at least partially cast out of a first material and has a plurality of support regions adapted to support an inner casing. The outer casing can be at least one support region that has a metal insert, made of a second material, with a flaring portion for retaining the metal insert in the casting of the outer casing. The second material has a greater hot strength than the first material. The support region can include a guide for limiting the movement of the inner casing in the outer casing. | 04-28-2011 |
20110116915 | Steam Turbine Having a Cooling Apparatus - A turbomachine comprising a rotor, an inner housing, and an outer housing is proposed. The inner housing is arranged around the rotor and the outer housing is arranged around the inner housing, An encapsulation is arranged around the inner housing. An annular channel and holes into a chamber are provided between the encapsulation and the inner-housing outer surface, and steam flows out again via holes which are situated in the encapsulation. | 05-19-2011 |
20110123323 | ATTACHING CERAMIC MATRIX COMPOSITE TO HIGH TEMPERATURE GAS TURBINE STRUCTURE - An assembly for use in a gas turbine engine has an underlying metal sheet, and at least one ceramic matrix composite tile attached to the underlying metal sheet with at least one fastener assembly. The panel fastener assembly includes a fastener having a threaded portion extending rearwardly from a head, which has a frustoconical surface facing the threaded portion. The frustoconical surface is received in a frustoconical bore in the ceramic matrix composite panel. A bushing is positioned on an opposed side of the metal sheet from the ceramic matrix composite panel. The bushing has a flange extending away from the metal sheet. A sleeve is received about the threaded portion of the fastener, and extends away from the panel, beyond the metal sheet. The sleeve has a lip extending radially outwardly toward the flange on the bushing, such that the flange on the bushing extends beyond a space defined between the lip and a seating surface on the bushing. A wave spring is received within the cavity. | 05-26-2011 |
20110135457 | MOLTEN METAL PUMP ROTOR - A molten metal pumping device is disclosed that comprises a pump base including at least one input port, a pump chamber, a chamber wall, and a discharge leading to an output port. A rotor is retained within the chamber and is connected to a rotor shaft. The rotor is a dual-flow (or mixed-flow) rotor, directing molten metal both into the chamber and out of the chamber, where it ultimately exits through the discharge. The dual-flow rotor has a recess to permit high amounts of molten metal to enter the pump chamber. | 06-09-2011 |
20110142606 | QUICK SUBMERGENCE MOLTEN METAL PUMP - A pump for transferring molten metal includes an intake tube, a motor, a rotor positioned at least partially within the bottom end of the intake tube, a rotor shaft positioned at least partially in the intake tube, the rotor shaft having a first end attached to the motor and a second end attached to the rotor. An overflow conduit is attached to the intake tube. The pump does not include a pump housing and preferably does not include a superstructure, so it is relatively small, light and portable. In use, the motor drives the rotor shaft and rotor to generate a flow of molten metal upward into the intake tube and into the overflow conduit where it is discharged. | 06-16-2011 |
20110142607 | CENTRIFUGAL COMPRESSOR FOR WET GAS ENVIRONMENTS AND METHOD OF MANUFACTURE - A centrifugal compressor comprises at least one stage suited to separate a liquid phase and a gas phase with the aid of at least one of a hydrophobic, super-hydrophobic, hydrophilic or super-hydrophilic surface layer, wherein the hydrophobic and/or super-hydrophobic surface layer is disposed on at least one of an inlet guide vane, impeller, return channel straight hub, or exiting hub bend; and the hydrophilic and/or super-hydrophilic surface is disposed on at least one of the impeller casing, diffuser casing, exiting casing bend, return channel straight hub, exiting hub bend, collection point, or drain. | 06-16-2011 |
20110150643 | Architecture of a Compressor Rectifier - The present invention relates to a turbine engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule support | 06-23-2011 |
20110171016 | AUSTENITIC DUCTILE CAST IRON - The invention provides an austenitic ductile cast iron alloy composition including about 2.2% to about 2.4% by weight carbon; about 3.5% to about 4.0% by weight silicon; about 28% to about 29% by weight nickel; about 2.5% to about 3.0% by weight chromium; about 0.9% to about 1.1% by weight molybdenum; and greater than about 50% iron, wherein percentages are based on the overall weight of the composition. The invention further provides articles, such as turbocharger housings, prepared using the inventive alloys. | 07-14-2011 |
20110211945 | METHOD FOR THE MANUFACTURE OF A CIRCULAR REVOLUTION THERMOMECHANICAL PART INCLUDING A TITANIUM-BASED LOAD-BEARING SUBSTRATE LINED WITH STEEL OR SUPERALLOY, A TURBOMACHINE COMPRESSOR HOUSING WHICH IS RESISTANT TO TITANIUM FIRE OBTAINED ACCORDING TO THIS METHOD - A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). An explosion cladding of a circular blank made of steel, or steel alloy, or superalloy which is incombustible in the presence of a titanium fire is accomplished on a circular blank made from titanium or titanium alloy. | 09-01-2011 |
20110217160 | COMPONENT COMPRISING A RESIN MATRIX - A composite material comprises plies | 09-08-2011 |
20110268566 | METHOD FOR THE MANUFACTURE OF A CIRCULAR REVOLUTION THERMOMECHANICAL PART INCLUDING A TITANIUM-BASED LOAD-BEARING SUBSTRATE LINED WITH STEEL OR SUPERALLOY, A TURBOMACHINE COMPRESSOR HOUSING WHICH IS RESISTANT TO TITANIUM FIRE OBTAINED USING THIS METHOD - A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). A ring made of steel, steel alloy, or superalloy which is incombustible in the presence of a titanium fire is ring roll-bonded with a ring made from titanium or titanium alloy. | 11-03-2011 |
20110274538 | CERAMIC GAS TURBINE SHROUD - An example gas turbine engine shroud includes a first annular ceramic wall having an inner side for resisting high temperature turbine engine gasses and an outer side with a plurality of radial slots. A second annular metallic wall is positioned radially outwardly of and enclosing the first annular ceramic wall and has a plurality of tabs in communication with the slot of the first annular ceramic wall. The tabs of the second annular metallic wall and slots of the first annular ceramic wall are in communication such that the first annular ceramic wall and second annular metallic wall are affixed. | 11-10-2011 |
20110280717 | STEAM DEVICE - In one embodiment, a steam device includes a high-temperature member and a low-temperature member. One surface of the high-temperature member is exposed to high-temperature steam, and the other surface is cooled by cooling steam having a temperature lower than the high-temperature steam. The low-temperature member is disposed to face the high-temperature member with a passage for the cooling steam therebetween and is formed of a material having a heat resistance lower than that of the high-temperature member. The steam device has at least one high-reflectance film selected from a first high-reflectance film, which is formed on the surface of the high-temperature member which is exposed to the high-temperature steam and has a higher reflectance with respect to infrared rays than the high-temperature member, and a second high-reflectance film, which is formed on the surface of the low-temperature member facing the high-temperature member and has a higher reflectance with respect to infrared rays than the low-temperature member. | 11-17-2011 |
20110286840 | LIQUID RING PUMP WITH LINER - A liquid ring pump is provided that includes an annular housing having an inner surface forming a housing cavity. The annular housing is filled with an operating fluid during operation of the pump. The operating fluid forms an eccentric liquid ring in the annular housing during operation of the pump. A rotor is disposed in the housing cavity and includes a plurality of rotor blades. A shaft extends into the annular housing into the housing cavity. The plurality of rotor blades extend radially outward from the shaft toward the inner surface of the annular housing. A liner formed from a corrosion resistant material is disposed substantially flush with at least a portion of the annular housing inner surface opposite a plurality of rotor blade ends. | 11-24-2011 |
20110293411 | HONEYCOMB CORE STRUCTURE FOR USE IN A STRUCTURAL PANEL FOR A JET ENGINE NACELLE - The invention relates to a honeycomb core structure ( | 12-01-2011 |
20120003086 | TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME - A turbine nozzle is provided and includes a first ring having a first microstructure, a vane extending from the first ring, a first porous zone between the first ring and the vane that is more porous than the first microstructure to attenuate thermo-mechanical fatigue cracking between the vane and the first ring. Methods of manufacturing the turbine nozzle are also provided. | 01-05-2012 |
20120014787 | THERMAL EXPANSION CHAMBERS FOR AIRTIGHT CONTAINERS - A hydraulic pump has a rotor and a hollow housing with a main interior chamber. The rotor is rotatably mounted in the main interior chamber. A smaller interior chamber is separated from the main interior chamber such that the smaller interior chamber retains gas therein when the main interior chamber is filled with a liquid. | 01-19-2012 |
20120034076 | FAN CASE CONTAINMENT SYSTEM AND METHOD OF FABRICATION - Composite article includes a generally cylindrical body having an internal grid structure interleaved with casing layers formed of reinforcing fibers disposed in a resin matrix. The composite article may be utilized in a fan case containment system for aircraft engine applications. Methods for fabricating the composite article are also provided. | 02-09-2012 |
20120045322 | VACUUM PUMP - A multi stage vacuum pump for pumping corrosive fluid with a first flow section of material less resistant to corrosion than the material of a second flow section downstream of the first flow section. | 02-23-2012 |
20120082541 | GAS TURBINE ENGINE CASING - An engine casing for a gas turbine engine, such as, but not limited to, a gas turbine engine fan case, is disclosed which includes an annular case shell formed of a substrate material that is at least partially coated by a nanocrystalline metal coating. A method of manufacturing such an engine casing is also provided. The present engine casing provides improved containment capability in the event of a blade release or other failure during operation of the engine. | 04-05-2012 |
20120099979 | PORTABLE BLOWER WITH WEAR RESISTANT DISCHARGE END - A portable blower having a propulsion unit for continuously generating a supply of pressurized fluid and a conduit assembly for controllably directing fluid from the propulsion unit to and through a discharge opening on the conduit assembly. The discharge opening is bounded by a rim, defined at least partially by a discrete component made from a first material. The conduit assembly has a first portion made from a second material to which the discrete component is operatively connected. The first material is at least one of: a) more resistant to abrasive wear than the second material; b) more resistant to impact than the second material; and c) harder than the second material. | 04-26-2012 |
20120099980 | PLASTIC HOUSING OF A RADIAL FLOW COMPRESSOR - The invention relates to a housing ( | 04-26-2012 |
20120099981 | AEROENGINE FAN CASING MADE OF COMPOSITE MATERIAL, AND A METHOD OF FABRICATING IT - An aeroengine fan casing is made of composite material comprising fiber reinforcement densified by a matrix. The casing ( | 04-26-2012 |
20120099982 | TURBINE DISTRIBUTOR ELEMENT MADE OF CMC, METHOD FOR MAKING SAME, DISTRIBUTOR AND GAS TURBINE INCLUDING SAME - A turbine nozzle element including an inner annular platform sector, an outer annular platform sector, and at least one vane extending between the platform sectors and connected to both of them. The nozzle element includes a single piece of composite material including fiber reinforcement densified by a matrix that is at least partially ceramic, and the fiber reinforcement includes a fiber structure that is woven by three-dimensional or multi-layer weaving, and that presents continuity throughout the volume of the nozzle element and throughout the periphery of the vane. | 04-26-2012 |
20120107110 | THERMAL PROTECTION COATING FOR A TURBINE-ENGINE PART, AND A METHOD OF MAKING IT - A thermal protection coating, in particular for a turbine-engine part ( | 05-03-2012 |
20120134793 | BLOOD PUMP WITH SEPARATE MIXED-FLOW AND AXIAL-FLOW IMPELLER STAGES, COMPONENTS THEREFOR AND RELATED METHODS - A rotordynamic pump for delivering continuous flow of fluids, such as blood, is provided. In one embodiment, the pump includes a stator housing having an inlet and an outlet. A rotor hub is disposed within the stator housing having a first, mixed-stage impeller and a second, axial-flow stage impellers. One or more stator vanes and extend radially inwardly from the stator housing. In one particular embodiment, the second stage impeller is disposed nearer to the outlet than to the inlet. The stator vanes may include a first set of stator vanes disposed between the first and second stage impellers, and a second set of stator vanes positioned between the second stage impellers and the outlet. | 05-31-2012 |
20120148391 | CENTRIFUGAL COMPRESSOR - A centrifugal compressor is equipped with a resin housing, that is made in a manner such that compression efficiency is not lost and merits such as weight and cost reduction are not cancelled out. The turbo charger housing comprises a volute section, a channel formation section, and an impeller that is fixed in the center of the channel formation section to a rotating shaft. An annular shroud is disposed in a recess formed on the inner wall of the channel formation section. The annular shroud forms the outer walls of a channel and a diffuser for compressed gas. The edge of the annular shroud spaced from a partition wall, which forms a portion of a bearing housing. If the resin housing undergoes thermal deformation, the dimensions of a gap between the annular shroud and the curved profile of a blade is maintained. | 06-14-2012 |
20120148392 | COMPOSITE FAN CONTAINMENT CASE ASSEMBLY - A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area. | 06-14-2012 |
20120156020 | METHOD OF REPAIRING A TRANSITION PIECE OF A GAS TURBINE ENGINE - A method of weld repairing an air-cooled aft frame of a transition piece of a gas turbine engine. The transition piece has an interior surface coated with a ceramic coating. The aft frame has a surface with cooling holes therein and from which cracks have propagated. The method includes removing the transition piece from the engine and, without removing the ceramic coating or the aft frame from the transition piece, weld repairing the cracks by performing a laser beam welding technique that deposits a filler material on the surface but does not close the cooling holes in the surface. The surface of the aft frame can be machined to remove excess filler material prior to re-installing the transition piece in a gas turbine engine. | 06-21-2012 |
20120177488 | PROCESS FOR JOINING SILICON-CONTAINING CERAMIC ARTICLES AND COMPONENTS PRODUCED THEREBY - A process for joining silicon-containing ceramic articles, and particularly ceramic articles and CMC articles that contain both silicon carbide and free silicon. The process entails providing a reactive metal-containing braze material between the articles, and then heating the braze material and the articles to react the reactive metal with the silicon within the articles to form a brazement containing a silicide phase of the reactive metal. The brazement and articles are then cooled to produce a component comprising the two articles and the silicide phase-containing brazement. The process is preferably carried out at temperatures below that which would thermally degrade constituents of the articles, and more preferably below the melting point of silicon. | 07-12-2012 |
20120183394 | TURBOMACHINE SHROUD - An example turbomachine shroud assembly includes an annular shroud configured to receive a rotating component. A radially outer surface of the annular shroud establishes positioning slots and relief slots. The positioning slots are configured to receive a support finger that limits radial movement of the annular shroud. The relief slots are different than the positioning slots. | 07-19-2012 |
20120195745 | COMPRESSOR NOZZLE STAGE FOR A TURBINE ENGINE - A single-piece compressor nozzle stage for a turbine engine, the stage comprising two coaxial rings, connected together by radial vanes, the inner ring including an annular cavity for housing damper means for damping vibration by friction, which damper means are secured to an annular abradable-material support. | 08-02-2012 |
20120207592 | TURBOMOLECULAR PUMP, AND METHOD OF MANUFACTURING ROTOR - A turbomolecular pump includes: a rotor ( | 08-16-2012 |
20120224953 | External Segmented Shell Capable of Correcting For Rotor Misalignment in Relation to the Stator - The invention relates to a housing for covering the ends of a row of rotor blades of an axial turbomachine compressor, the housing being provided with a sealing device between the blade tips and the housing. It comprises a shell segmented along its circumference, each segment being fixed to the housing by a series of elastomeric elements in a recess in the shape of a channel cut into the inner surface of the housing. In this way, in the event of misalignment of the rotor relative to the stator, the rotor blades coming into contact with sections of the shell will be able to move to compensate for this misalignment while reducing the frictional forces generated by contact between the blades and the shell. In the event of alignment being re-established the segments of the shell will be able to resume their initial position because of the elastic behaviour of the elements. | 09-06-2012 |
20120230815 | VENTILATION FAN - A ventilation fan arranged to reduce vibrations includes an impeller rotating around a center axis, a motor portion arranged to rotate the impeller, a motor supporting portion arranged to support the motor portion, and a housing arranged to accommodate the impeller and the motor portion. The motor supporting portion includes a substantially disk-shaped base portion, and a substantially cylindrical bearing holding portion axially extending with the center axis as the center. At least the base portion is made from resin. On the surface of the base portion, a plurality of recessed portions which are axially recessed are arranged in the form of a net, a staggered pitch, a grid, or a honeycomb. A flat portion of the base portion excluding the recessed portions does not have a continuous region extending in a straight line radially from the center of the base portion. | 09-13-2012 |
20120243981 | CAST TURBINE CASING AND NOZZLE DIAPHRAGM PREFORMS - Various turbine component preforms are disclosed having near-net shape features. In one embodiment, a turbine casing preform is disclosed. The turbine casing preform includes an as-cast body comprising a partially cylindrical wall section of a turbine casing, the wall section having an inner surface and an outer surface. The turbine casing preform also includes a circumferentially-extending vane slot formed in the wall section on the inner surface. In another embodiment, a turbine nozzle diaphragm preform is disclosed. The turbine nozzle diaphragm preform includes an as-cast body comprising a partially-cylindrical wall section of a turbine nozzle diaphragm having an inner surface and an outer surface. The turbine nozzle diaphragm preform also includes an as-cast, circumferentially-extending seal member projecting from one of the outer surface or inner surface. | 09-27-2012 |
20120243982 | COMPRESSOR AND ASSEMBLY METHOD THEREOF - Provided is a compressor that is capable of, with a simple configuration, facilitating the insertion operation of a compressor bundle by reliably preventing tilting thereof during insertion into a chamber; and that also makes it possible to reduce a roller size without increasing the contact pressure of rollers for sliding the compressor bundle. A small tilt sensor that detects a relative angle difference θ of the compressor bundle with respect to the bundle casing is provided at at least one location in the compressor bundle to be inserted into the chamber inside the bundle casing. In addition, the weight of the compressor bundle during the insertion into the chamber is supported by rollers provided at a bottom portion near the front end of the compressor bundle by making the rollers come in contact with an inner circumferential wall surface of the chamber. | 09-27-2012 |
20120251309 | CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY AN AXIAL CONTACT - Composite material turbine nozzle blade including an airfoil ( | 10-04-2012 |
20120251310 | METHOD FOR PRODUCING AN ABRADABLE COATING ON A TURBOMACHINE - In a method for producing an inlet coating ( | 10-04-2012 |
20120263584 | Compressor Housing of a Radial Compressor - A compressor housing ( | 10-18-2012 |
20120275913 | EXTERNAL THREADED MOUNT ATTACHMENT FOR FAN CASE - An example composite fan case assembly includes a composite fan case body disposed on an axis. The fan case body has a radially inner surface and a radially outer surface. There is at least one mounting attachment to receive a threaded member. The at least one mounting attachment includes a base component and a spool component. The base component extends through an opening in the fan case body from the radially outer surface and toward the radially inner surface of the fan case body. The base component including a base portion, a boss having a non-cylindrical profile, and a cylindrical portion. The mounting attachment also includes a spool component disposed on the radially outer surface and attached to the base component. The spool component receives at least a portion of the base component. An outer surface of the cylindrical portion and an inner surface of the spool component are threaded and correspondingly mate to lock the spool component relative to the base component. | 11-01-2012 |
20120282086 | NICKEL-BASE ALLOY - The invention is a class of nickel-base alloys for gas turbine applications, comprising, by weight, about 13.7 to about 14.3 percent chromium, about 5.0 to about 10.0 percent cobalt, about 3.5 to about 5.2 percent tungsten, about 2.8 to about 5.2 percent titanium, about 2.8 to about 4.6 percent aluminum, about 0.0 to about 3.5 percent tantalum, about 1.0 to about 1.7 percent molybdenum, about 0.08 to about 0.13 percent carbon, about 0.005 to about 0.02 percent boron, about 0.0 to about 1.5 percent niobium, about 0.0 to about 2.5 percent hafnium, about 0.0 to about 0.04 percent zirconium, and the balance substantially nickel. The nickel-base alloys may be provided in the form of useful articles of manufacture, and which possess a unique combination of mechanical properties, microstructural stability, resistance to localized pitting and hot corrosion in high temperature corrosive environments, and high yields during the initial forming process as well as post-forming manufacturing and repair processes. | 11-08-2012 |
20120294709 | TURBINE HOUSING OF AN EXHAUST-GAS TURBOCHARGER - A turbine housing of an exhaust-gas turbocharger includes an outer housing, an inner housing, and a tubular fitting which is formfittingly connected to the inner housing and has a flange collar for attachment of a bearing case of a turbine wheel. The inner housing traverses the fitting and has an end portion which is bent radially outwards about the flange collar. A press ring is arranged upon the end portion for additional securement of the inner housing in place. | 11-22-2012 |
20120301286 | METHOD FOR REPAIRING A FLANGE OF A HOUSING - A method of repairing a flange of a casing, or a casing made of aluminum, for a turbine engine or an airplane turboprop or turbojet, the flange including at least one through hole for passing a bolt for fastening equipment. The method includes: forming a spot face in the flange around the hole for passing the bolt; anodizing the bottom surface of the spot face; placing a washer on the spot face; and fastening the washer to the flange using adhesive. | 11-29-2012 |
20120315133 | NI-BASED ALLOY FOR CASTING USED FOR STEAM TURBINE AND CASTING COMPONENT OF STEAM TURBINE - An Ni-based alloy for casting used for a steam turbine of an embodiment contains in percent (%) by mass C (carbon): 0.01 to 0.1, Cr (chromium): 15 to 25, Co (cobalt): 10 to 15, Mo (molybdenum): 5 to 12, Al (aluminum): 0.5 to 2, Ti (titanium): 0.3 to 2, B (boron): 0.001 to 0.006, Ta (tantalum): 0.05 to 1, Si (silicon): 0.1 to 0.5, Mn (manganese): 0.1 to 0.5, and the balance of Ni (nickel) and unavoidable impurities. | 12-13-2012 |
20120328427 | FIRESHIELD FASTENER HOOD - A fireshield fastener hood and method of bonding a cover to a substrate therefor. | 12-27-2012 |
20120328428 | CEMENTLESS PUMP FOR PUMPING MOLTEN METAL - In a cementless pump for pumping molten metal, support structure is suspended above the molten metal. A motor is supported by the support structure. A shaft is fastened to the motor. An impeller is mounted to a lower end of the shaft. A refractory base is supported in the molten metal and includes at least one impeller chamber in which the impeller is rotated and at least one discharge passageway. The base includes through holes. Support posts are each fastened to the support structure and to the base. Refractory sleeves are each disposed in one of the through holes. Post fastening members fasten the lower ends of the posts to the base without cement. A portion of each of the post fastening members is located inside the refractory sleeve. Also featured is a method of replacing posts in a cementless pump for pumping molten metal. | 12-27-2012 |
20130004306 | CHORDAL MOUNTING ARRANGEMENT FOR LOW-DUCTILITY TURBINE SHROUD - A shroud apparatus for a gas turbine engine includes: a shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface, wherein the shroud segment includes: a radially-inward facing chordal forward mounting surface; and a radially-inward facing chordal aft mounting surface; and an annular case surrounding the shroud segment, the case including: a radially-outward facing chordal forward bearing surface which engages the forward mounting surfaces; and a radially-outward facing chordal aft bearing surface which engages the aft mounting surface of the shroud segment. | 01-03-2013 |
20130011248 | REDUCTION IN THERMAL STRESSES IN MONOLITHIC CERAMIC OR CERAMIC MATRIX COMPOSITE SHROUD - A shroud for use in a gas turbine engine has a ring with a plurality of protrusions and a plurality of slots and each of the protrusions having an arc length and parallel sides. | 01-10-2013 |
20130011249 | MULTI-LAYER FILTER, GAS TURBINE INCLUDING A MULTI-LAYER FILTER, AND PROCESS OF FILTERING - A multi-layer filter, a gas turbine including a multi-layer filter, and a process of filtering are disclosed. The multi-layer filter includes a nano-fiber layer positioned to receive an airflow, a coalescing base medium layer, and a membrane layer. The coalescing base medium and the membrane layer are positioned for the airflow to travel through the nano-fiber layer and the coalescing base medium layer, then through the membrane layer. The gas turbine includes an inlet and the multi-layer filter in a filter portion. The process includes positioning the multi-layer filter and directing an airflow through the multi-layer filter | 01-10-2013 |
20130028719 | CONCRETE VOLUTE PUMP - A centrifugal pump is provided capable of pumping liquid volume flow rates of at least 20 m3/sec. The pump includes a centrifugal impeller rotatable about an axis and operable to direct a liquid towards a concrete volute arranged around the impeller. The pump further includes fixed fin-like elements arranged between the impeller and the volute. The elements form a discontinuous barrier around the impeller and are effective to reduce uneven radial thrusts exerted by the water on the centrifugal impeller, whilst limiting the water flow rate in a simple and economic manner. | 01-31-2013 |
20130045094 | HIGH-VACUUM PUMP - A high-vacuum pump comprises a plurality of pumping stages, each comprising a plurality of mutually cooperating elements, including at least one rotating rotor element and one stationary stator element. At least one of the elements of at least one of the pumping stages is made of a plastic material reinforced with short fibres, dispersed in chaotic and substantially random manner inside the matrix of plastic material. Use of a plastic material reinforced with short fibres allows making the at least one element by injection molding and allows manufacturing the vacuum pump with considerably reduced production costs if compared to the conventional vacuum pumps. | 02-21-2013 |
20130064658 | COMPRESSOR CASE LINING - A lining for a compressor case in use with a gas turbine engine compressor is provided. The compressor includes a compressor casing, which is generally comprised of a first and second half. Inside the casing is a plurality of vanes attached to a plurality of vane bands. The vane bands are affixed to the interior of the compressor casing. A lining, comprising a carbon fiber reinforced-type material is applied to the interior of the compressor casing over the vane bands. The lining allows a minimal clearance to be between the lining and wheel blade tips spinning within the compressor casing. The carbon fiber in the lining allows the lining to withstand a high number of temperature cycles due to the use of the compressor and the gas turbine engine. | 03-14-2013 |
20130094951 | MID TURBINE FRAME (MTF) FOR A GAS TURBINE ENGINE - A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of airfoil sections between an outer ring and an inner ring. A spring biased tie-rod assembly is mounted through at least one of the multiple of airfoil sections. | 04-18-2013 |
20130101406 | HIGH PRESSURE MOLDING OF COMPOSITE PARTS - Composite pre-forms are molded at high pressure to form composite parts that can be used in place of metal-based high performance parts, such as the outlet guide vanes found in turbofan jet engines. The composite pre-forms include two different fiber orientations that are co-molded in a resin matrix at high pressures to provide composite outlet guide vanes and other high performance parts. Chambers within the composite part are optionally formed during molding of the pre-form at high pressures. | 04-25-2013 |
20130108426 | LOW NICKEL AUSTENITIC STAINLESS STEEL | 05-02-2013 |
20130108427 | Co-Injected Composite Shell For An Axial Turbomachine Compressor | 05-02-2013 |
20130115070 | BLOOD PUMP INCLUDING A ROTOR - A blood pump includes a rotor mounted in a pump housing via a bearing. The housing includes a metal rod extending from the outer wall of the housing towards the inner side of the housing. The rod allows dissipating heat and has a stabilising action. | 05-09-2013 |
20130136588 | FIBROUS STRUCTURE FORMING A FLANGE AND A COUNTER-FLANGE - A fibrous structure for fabricating a composite part including a matrix reinforced by the fibrous structure, the fibrous structure being made by three-dimensional weaving and presenting a main portion and a margin adjacent to the main portion. The margin presents a thickness greater than the thickness of the main portion and the margin includes a first portion arranged in continuity with the main portion and a second portion superposed on the first portion to constitute extra thickness, the margin thus being configured to be folded towards the second portion so that the first and second portions respectively form a flange and a counter-flange for fastening the part. | 05-30-2013 |
20130142637 | LOW RHENIUM SINGLE CRYSTAL SUPERALLOY FOR TURBINE BLADES AND VANE APPLICATIONS - A low rhenium nickel-base superalloy for single crystal casting that exhibits excellent high temperature creep resistance, while also exhibiting other desirable properties for such alloys, comprises 5.60% to 5.80% aluminum by weight, 9.4% to 9.9% cobalt by weight, 4.9% to 5.5% chromium by weight, 0.08% to 0.35% hafnium by weight, 0.50% to 0.70% molybdenum by weight, 1.4% to 1.6% rhenium by weight, 8.1% to 8.5% tantalum by weight, 0.60% to 0.80 titanium by weight, 7.6 to 8.0% tungsten by weight the balance comprising nickel and minor amounts of incidental impurity elements. | 06-06-2013 |
20130149126 | TREATED VALVE SEAT - An aluminum alloy turbine housing includes an inlet for exhaust, a turbine wheel space configured to receive exhaust via the inlet, a wastegate opening configured to receive exhaust via the inlet and to provide received exhaust to a wastegate chamber, and a locally hardened valve seat surrounding the wastegate opening. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed. | 06-13-2013 |
20130149127 | Structural Platforms for Fan Double Outlet Guide Vane - A structural platform comprises a first end, a second end, a first side wall and a second side wall, a platform body extending between the first end and the second end and further between the first side wall and the second side wall, a first fillet joining the first side wall and the platform body, a second fillet joining the second side wall and the platform body, the sidewalls being curved. | 06-13-2013 |
20130156565 | Boron-Containing Nucleating Agent for Polyphenylene Sulfide - A boron-containing nucleating agent is provided for use with a polyarylene sulfide. The boron-containing nucleating agent can have low crystallinity, a small particle size, and a large specific surface area. By selectively controlling certain aspects of the nucleating agent, the crystallization properties of a thermoplastic composition including the nucleating agent and a polyarylene sulfide can be significantly improved. For instance, the recrystallization temperature can be increased, which can allow the “cooling time” during a molding cycle to be substantially reduced. Through use of the boron-containing nucleating agent the recrystallization temperature can be greater than about 231° C. | 06-20-2013 |
20130177407 | ROTOR, A STEAM TURBINE AND A METHOD FOR PRODUCING A ROTOR - A rotor, a steam turbine having a rotor, and a method of producing a rotor are disclosed. The rotor disclosed includes a shaft high pressure section. The high pressure section includes a first high pressure section, a second high pressure section, the second high pressure section being joined to the first pressure section, and a third high pressure section, the third high pressure section being joined to the second high pressure section. At least a portion of the second high pressure section is formed of a high-chromium alloy steel comprising 0.1-1.2 wt % of Mn, up to 1.5 wt % of Ni, 8.0-15.0 wt % of Cr, up to 4.0 wt % of Co, 0.5-3.0 wt % of Mo, 0.05-1.0 wt % of V, 0.02-0.5 wt % of Cb, 0.005-0.15 wt % of N, up to 0.04 wt % of B, up to 3.0 wt % of W, and balance Fe and incidental impurities. | 07-11-2013 |
20130189092 | GAS TURBINE ENGINE STATOR VANE ASSEMBLY WITH INNER SHROUD - A stator vane assembly includes a vane having an inner end. In one example, the vane is aluminum. An inner shroud has an aperture receiving the inner end. A flexible material secures the inner end to the inner shroud. The material has an inner surface opposite the vane providing a seal land in one example. The inner shroud provides an arcuate inner shroud segment, which is constructed either cast aluminum or stamped sheet steel. An inner shroud segment has an arcuate wall providing multiple apertures, for example. First and second flanges are integral with and extending radially inwardly from a concave side of the wall. | 07-25-2013 |
20130202424 | CONFORMAL LINER FOR GAS TURBINE ENGINE FAN SECTION - A fan section of a gas turbine engine includes a fan case structure having a first coefficient of thermal expansion. A fan blade is arranged within the fan case structure and has a second coefficient thermal expansion. A continuous ring-shaped liner surrounds the fan blade and includes a third coefficient of thermal expansion that is substantially similar to the second coefficient of thermal expansion and substantially different than the first coefficient of thermal expansion. An elastomeric adhesive operatively connects the liner to the fan case structure. The adhesive is configured to accommodate diametrical change in the liner and maintain a desired radial tip clearance throughout various fan section operating temperatures. | 08-08-2013 |
20130202425 | Turbojet engine case, notably intermediate case - The present invention relates to an annular case ( | 08-08-2013 |
20130216367 | CASE WITH BALLISTIC LINER - A case for a gas turbine engine includes a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. A method of manufacturing the case includes winding the plurality of unidirectional roving fiber layers around the plurality of non-crimp fabric layers. | 08-22-2013 |
20130216368 | TURBINE STATOR AIRFOILS WITH INDIVIDUAL ORIENTATIONS - In accordance with an exemplary embodiment, a turbine stator component includes a first endwall; a second endwall; a first stator airfoil coupled between the first and second endwalls; and a second stator airfoil adjacent to the first airfoil and coupled between the first and second endwalls. The first stator airfoil has first crystallographic primary and secondary orientations. The second stator airfoil has second crystallographic primary and secondary orientations, the first crystallographic primary and secondary orientations being different from the second crystallographic primary and secondary orientations. | 08-22-2013 |
20130224005 | COMPRESSION SLEEVE SEAL - A seal for a turbine casing is provided. The turbine casing includes a plurality of sections joined at flanges provided on each section. Each flange includes a bore and a counterbore. The seal comprises a compression sleeve seal having a length that is greater than a counterbore-to-counterbore length of two flanges; a fastener configured to extend through the compression sleeve seal; and a nut threadable on each end of the fastener. The compression sleeve seal is compressible between each flange and each nut to create a first seal and is radially extensible to create a second seal against each bore. | 08-29-2013 |
20130236302 | IN-SITU GAS TURBINE ROTOR BLADE AND CASING CLEARANCE CONTROL - A method and system for protecting the rotor blade tips of rotary machines, particularly the compressors of gas turbine engines, comprising a rotor assembly having a plurality of circumferentially spaced-apart rotor blades, with each blade extending radially outwardly from an inner wheel disk; a stator assembly comprising one or more rows of spaced-apart vanes extending between adjacent rows of the rotor blades; a casing extending circumferentially around the rotor and stator assemblies; and an abradable ceramic coating applied to selected areas of the interior cylindrical surface of the rotor casing to thereby provide a minimum clearance between the casing and rotor blades during start up and to thereafter ensure an effective compressor seal for compressed gas flow. | 09-12-2013 |
20130251515 | THERMAL ISOLATION APPARATUS - A thermal isolation apparatus is provided and includes an annular casing surrounding a turbine bucket stage and defining an annular recess from an interior facing surface thereof, an annular shroud disposed within the casing to provide for a predefined clearance about rotating bucket tips of the turbine bucket stage, the shroud including an annular main member and an annular flange extending from an outwardly facing surface of the main member and being sized to fit within the recess and a thermal barrier formed of porous material, which is interposed between opposing surfaces of the casing and the flange within the recess. | 09-26-2013 |
20130272862 | METHOD FOR MANUFACTURING FAN BLADE AND FAN USING SUCH FAN BLADES - A method for manufacturing a fan blade includes the steps of, firstly, providing a mold. Then a mixture of metal powder and adhesive material is injected into the mold to forming a green body of the blade. Next, the adhesive material is removed from the green body of the blade. Finally, the green body of the blade is sintered to form the fan blade. A fan with such blades is also provided. | 10-17-2013 |
20130302153 | AIR CIRCULATION FAN USED IN LIGHT STEEL FRAME - An air circulation fan used in a light steel frame includes a top base, a circuit assembly, a shroud, a driving source, and a blade set. A pivoting portion of the shroud is pivotally connected to a combining portion of the top base, so that the shroud can pivotally hung on the top base. When the shroud is combined with the top base, the two connecting portions of the shroud are inserted into two through-holes of an accommodating casing with a second elastic piece of each through-hole abutting against a first elastic piece of each combining portion, thereby electrically connecting the circuit assembly to the driving source. When the shroud is separated from the top base, the connecting portions are removed from the through-holes with the second elastic piece being separated from the first elastic piece, thereby shutting off the electrical connection between the circuit assembly and the driving source. | 11-14-2013 |
20130302154 | CASING - A containment case for a gas turbine including: a cylindrical outer casing extending about an axis and having a radially outer and a radially inner surface; a coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing; and an array of ribs extending radially from the inner skin towards the axis. The case for can have the coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing by a galvanic isolation layer. | 11-14-2013 |
20130309076 | Rotating Body of Vacuum Pump, Fixed Member Disposed Opposite Rotating Body, and Vacuum Pump Provided with Rotating Body and Fixed Member - A rotating body of a vacuum pump is partially constituted by a fiber-reinforced plastic and configured to exhaust gas by rotation. A corrosion-resistant layer is provided on the fiber-reinforced plastic portion which is the base material of the rotating body. A high-emissivity layer having a higher emissivity than the corrosion-resistant layer is provided on the corrosion-resistant layer. Fixed members facing the rotating body of the vacuum pump are each provided with a high-emissivity layer having a higher emissivity than the base material of the fixed members on the surfaces facing the fiber-reinforced plastic portion of the rotating body. | 11-21-2013 |
20130323040 | CENTRIFUGAL BLOWING FAN - A centrifugal blowing fan includes a back yoke made from metal, having a substantially bottomed cylindrical portion around a rotating shaft of a motor, an inner surface attached with a magnet of the motor mounted thereon and a flange portion disposed around a periphery of an opening of the cylindrical portion; and a cylindrical impeller made from resin, having a plurality of blades circumferentially arranged, an annular collar portion joined with first ends of the plurality of blades and a doughnut-shaped disk portion joined with second ends of the plurality of blades, wherein the disk portion has at least one fitting, and the flange portion has at least one fitted space receiving the at least one fitting so as to concentrically and fixedly connect the impeller and the back yoke. | 12-05-2013 |
20130336773 | METALLIC RAILS ON COMPOSITE FAN CASE - A composite fan case has a generally cylindrical composite shell, at least one band of sacrificial composite material circumscribing an outer surface of the composite shell, and a metallic rail mounted on the band of sacrificial material. Also disclosed is a method of construction the aforementioned case. | 12-19-2013 |
20130343884 | Impeller of Cooling Fan - An impeller of a cooling fan includes a metal base, a shaft and a plurality of plastic blades. The metal base includes a shaft-coupling portion, a first assembling portion apart from the shaft-coupling portion, and a flat portion between the shaft-coupling portion and the first assembling portion, wherein the flat portion oppositely has a first flat surface and a second flat surface, and a permanent magnet is mounted on the first flat surface. The shaft has a fixing end coupled with the shaft-coupling portion of the metal base. Each of the plastic blades has a second assembling portion coupled with the first assembling portion of the metal base. | 12-26-2013 |
20140023492 | INTEGRATED NACELLE INLET AND METALLIC FAN CONTAINMENT CASE - A fan nacelle includes a metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements. A gas turbine engine includes a metallic fan containment case. A core engine has a static engine structure housing a compressor section, a combustor section and a turbine section. The core engine is configured to receive core airflow. A fan is arranged within the metallic fan containment case. The fan is coupled to the core engine and is arranged in a bypass flowpath provided between the core engine and the metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements. | 01-23-2014 |
20140044532 | PROCESS FOR PRODUCING A TiAl GUIDE VANE RING FOR A GAS TURBINE AND A CORRESPONDING GUIDE VANE RING - Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising:
| 02-13-2014 |
20140050574 | RAM AIR FAN OUTER HOUSING - A ram air fan outer housing for directing air from a ram air fan rotor and air from a ram air bypass into a ram air fan outlet. The outer housing includes an outer cylinder and a plenum connected at a joint region. The outer cylinder is made of a laminate stacking sequence of at least four adjacent layers of plain-weave carbon-fiber fabric in an A-B-B-A sequence. The plenum is made of a laminate stacking sequence of at least eight adjacent plenum layers of plain-weave carbon-fiber fabric in an A-B-B-A-A-B-B-A sequence. The plenum is joined to the outer cylinder at a joint region, the joint region includes a transition section transitioning the laminate stacking sequence from the eight adjacent layers of the plenum walls to the four adjacent layers of the outer cylinder walls. | 02-20-2014 |
20140072421 | FAN CASE BALLISTIC LINER AND METHOD OF MANUFACTURING SAME - A method of manufacturing a fan case with a liner includes the steps of providing a preform having a circular cross-section with a cut and a first diameter, flexing the preform to reduce the first diameter to a second diameter, and adhering the preform to an inner surface of a fan case. A fan case for a gas turbine engine includes a fan case body having an inner surface. A preform is adhered to the inner surface and has a cut providing a gap. | 03-13-2014 |
20140086734 | METHOD AND SYSTEM FOR FABRICATING COMPOSITE CONTAINMENT CASINGS - A system and a method for making a composite containment casing are provided. The method includes providing a mandrel, applying at least one ply of a material about the mandrel to form a first annular facesheet, applying a plurality of core segments surrounding the first facesheet, forming a casing surrounding the core segments. and curing the facesheet, core segments, and casing together forming a unitary composite containment casing. Alternatively, the facesheet and the core segments can be formed and cured first, and then form and cure the outer casing to complete the manufacture of a unitary composite containment casing, | 03-27-2014 |
20140086735 | LOUVER BLADE - A louver blade comprises a blade body and a reinforcing member. The blade body is made of a plastic material, includes a first end portion and a second end portion opposite to the first end portion along a first axis, and is provided with two pivot connecting portions. Each of the pivot connecting portions is disposed on the first axis at a corresponding one of the first and second end portions and is adapted for pivotal connection with a louver frame to ensure accurate alignment when mounting. The reinforcing member is made of a metal material, is embedded in the blade body, and has an H-shaped cross section to enhance the structural strength of the louver blade. | 03-27-2014 |
20140119905 | FAN STRUCTURE - A fan structure includes a casing, a fan, and two elastic members. The casing has an accommodation space. The fan is located in the accommodation space. The fan has a first side and a second side opposite to each other. One of the two elastic members is sandwiched between the casing and the first side of the fan. The other one of the two elastic members is sandwiched between the casing and the second side of the fan. The two elastic members normally keep the fan away from the casing, so as to make the fan contact the casing through the two elastic members, thereby achieving a damping effect. | 05-01-2014 |
20140161600 | STATOR FOR GAS EXHAUST PUMP, METHOD FOR MANUFACTURING THE SAME, PUMP HAVING THE STATOR, AND MANUFACTURING METHOD AND ASSEMBLING METHOD OF THE SAME - There is provided a stator that can ensure safe rotation even if a width of a gap between a screw rotor and a stator is particularly smaller than that of a conventional one and can greatly increase a pumping performance of a pump. A stator of the present invention is formed of a metal and a PFA film is provided on an inner wall surface of a top end surface of a screw rotor. After coating the inner wall surface with PFA, followed by melting and remelting processes, the PFA film is formed to have a high smoothness. The stator is placed with a gap between the inner wall surface and the top end surface. If the PFA film of the present invention is provided in a predetermined manner, the width of the gap can be made significantly smaller than that of a conventional one. | 06-12-2014 |
20140161601 | METHOD FOR PRODUCING, REPAIRING AND/OR EXCHANGING A HOUSING, IN PARTICULAR AN ENGINE HOUSING, AND A CORRESPONDING HOUSING - The invention relates to a method for producing, repairing and/or exchanging a housing, in particular an engine housing of an aircraft engine, comprising at least two shells, between which a structural part is formed, wherein the method comprises the following step: layer-by-layer construction of the at least two shells jointly with the structural part by means of a generative manufacturing system, wherein the structural part comprises at least one porous structure and/or honeycomb structure. The invention relates furthermore to such a housing. | 06-12-2014 |
20140169956 | OVERMOLDED VANE PLATFORM - A vane includes a platform with a fixture overmolded by a sheath. | 06-19-2014 |
20140193249 | ELECTRICAL CONDUCTOR PATHS - A component, for example an aerofoil vane or other gas path structure in a gas turbine machine such as a gas turbine engine, in which an insulated electrical conductor path is embedded structurally integrally, and in which electromagnetic shielding, for the embedded electrical conductor path is provided structurally integrally. | 07-10-2014 |
20140199164 | NICKEL-BASED ALLOY AND TURBINE COMPONENT HAVING NICKEL-BASED ALLOY - A nickel-based alloy and a turbine component are disclosed. The alloy includes, by weight, between about 0.8% and about 1.3% hafnium, between about 5.7% and about 6.4% aluminum, between about 7.0% and about 10.0% cobalt, up to about 0.1% carbon, up to about 8.7% chromium, up to about 0.6% molybdenum, up to about 9.7% tungsten, up to about 0.9% titanium, up to about 0.02% boron, up to about 0.1% manganese, up to about 0.06% silicon, up to about 0.01% phosphorus, up to about 0.004% sulfur, up to about 0.02% zirconium, up to about 1.8% niobium, up to about 0.1% vanadium, up to about 0.1% copper, up to about 0.2% iron, up to about 0.003% magnesium, up to about 0.002% oxygen, up to about 0.002% nitrogen, and a balance nickel. The turbine component is a turbine bucket, a turbine nozzle, or any other suitable turbine component including the alloy. | 07-17-2014 |
20140234096 | TURBOMACHINE COMPONENT WITH AN EROSION AND CORROSION RESISTANT COATING SYSTEM AND METHOD FOR MANUFACTURING SUCH A COMPONENT - A turbomachine component of a stationary turbomachine includes a substrate made of high alloyed 10% to 18% chromium steels or titanium alloys or nickel base alloys or cobalt base alloys with a substrate surface and an erosion and corrosion resistant coating system. The coating system includes a first layer, which is deposited on the substrate surface of the turbomachine component and acts as a corrosion resistant layer and a second layer. The second layer is deposited on the first layer and acts as an erosion resistant layer, wherein the first layer is a Zr single layer and the second layer is a W/WC multilayer. | 08-21-2014 |
20140255174 | MANUFACTURE OF FULL RING STRUT VANE PACK - A vane assembly for a gas turbine engine is disclosed and includes a plurality of individual vane segments forming an annular ring. Each of the plurality of vane segments is formed of a ceramic matrix composite including at least one airfoil extending between an inner platform and an outer platform. An outer wrap is disposed about an outer periphery of the annular ring and over an interface between outer platforms of adjacent ones of the plurality of vane segments. | 09-11-2014 |
20140271161 | CERAMIC MATRIX COMPOSITE - A novel ceramic matrix composite is disclosed for forming components that are operable in high temperature environments such those in gas turbine engines and the like. The ceramic matrix composite can include at least one layer of non-crimped fibers positioned substantially parallel to one another. A relatively small diameter elastic fiber can be constructed to stitch the non-crimped fibers together and a ceramic matrix may be deposited around the at least one layer of non-crimped fibers. | 09-18-2014 |
20140271162 | PUMP CASING WITH PRE-STRESSED LINING - A method is described for forming a lining on an inner surface of a pump casing. The lining can protect the pump casing from corrosive and abrasive fluids. The method disclosed improves the durability and reliability of the lining by introducing a compressive pre-stress to the lining when the casing is not loaded such that during normal operation, the lining can be in a stress state near neutral and avoid failures related to excessive tensile strains. The method includes securing at least a portion of the casing in a stationary position and applying an external load to deform the casing. The method further includes depositing the lining onto the inner surface of the casing, curing the lining, and removing the external load to pre-stress the lining. | 09-18-2014 |
20140286765 | COMPOSITE AEROFOIL VANE - A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibres extending in a generally radial direction and a plurality of second reinforcing fibres extending in generally axial and circumferential directions. The second fibres are interlaced with the first fibres so as to form a more unified and integrated structure, and to prevent the first reinforcing fibres from moving relative to one another. | 09-25-2014 |
20140301836 | VANE ASSEMBLY AND METHOD OF MAKING THE SAME - A vane assembly for a gas turbine engine comprises at least one vane, a first platform and a second platform. The at least one vane has a first end and an opposite second end with the first end of the at least one vane being secured in a corresponding first aperture in the first platform, and the second end of the at least one vane being secured in a corresponding second aperture in the second platform. | 10-09-2014 |
20140308117 | Armoring Sealing Fins of TiAl Vanes by Induction Brazing Hard-Material Particles - A method for armoring TiAl vanes of turbomachines is disclosed. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by an inductive heating process. A TiAl vane for a turbomachine, in particular for an aircraft engine, is also disclosed. The TiAl vane includes a TiAl main part and an armor which consists of a mixture of hard materials and braze material. | 10-16-2014 |
20140314556 | Method of Fabricating a Turbine or Compressor Guide Vane Sector Made of Composite Material for a Turbine Engine, and a Turbine or a Compressor Incorporating Such Guide Vane Sectors - Single-airfoil vanes each having an inner platform, an outer platform, and an airfoil are obtained by three-dimensionally weaving a fiber blank in a single piece, by shaping the fiber blank to obtain a single-piece fiber preform, and by densifying the preform with a matrix to obtain a vane of composite material forming a single piece with inner and outer platforms incorporated therein. A plurality of vanes is assembled together at an intermediate stage of densification to form a multi-airfoil composite material guide vane sector for a turbine nozzle or a compressor diffuser and the assembled-together vanes are bonded together. | 10-23-2014 |
20140356150 | GRAIN MICROSTRUCTURE IN DAMPERS OF GAS TURBINE ENGINE - A damper for a gas turbine engine is provided. The damper comprises a first portion, a second portion, and a surface. The second portion angularly extends from the first portion to define an interior corner therebetween. The surface bounds the first portion, the second portion, and the interior corner. The damper further comprises a grain composition containing columnar grains and equiaxed grains. The equiaxed grains are disposed adjacent to the surface such that a volume of the columnar grains is less than a volume of the equiaxed grains in the grain composition. | 12-04-2014 |
20140356151 | HOLLOW-BLADE TURBINE VANE MADE FROM COMPOSITE MATERIAL, TURBINE OR COMPRESSOR INCLUDING A NOZZLE OR GUIDE VANE ASSEMBLY FORMED BY SUCH BLADES, AND TURBOMACHINE COMPRISING SAME - A turbine engine vane is made of composite material comprises a hollow airfoil with an internal passage extending along its entire length, an inner platform, and an outer platform. The airfoil is extended on the outside of the outer platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing. The attachment portions are formed by an attachment extending from the outer longitudinal ends of the pressure side wall and the suction side wall of the airfoil with continuity of the fiber reinforcing texture of the composite material between the walls and the attachment tabs. | 12-04-2014 |
20140369822 | Method for Producing Forged Components From A TiAl Alloy And Component Produced Thereby - The invention relates to a method for producing a component from a TiAl alloy, wherein the component is shaped by forging, in particular isothermal forging, and is subsequently subjected to at least one heat treatment, wherein in the first heat treatment the temperature is between 1100 and 1200° C. and is maintained for 6 to 10 hours and then the component is cooled. | 12-18-2014 |
20150010395 | Stator Blade Sector for an Axial Turbomachine with a Dual Means of Fixing - The present application relates to a stator blade sector configured to be fixed to a housing of an axial turbomachine, the sector having a plurality of blades with platforms juxtaposed, so as to describe an arc of a circle. At least one of the platforms comprises on its outer face a fixing screw and at least one other platform has no fixing screws, the platforms being fixed together at their adjacent edges. The application also relates to a stator or portion of stator having a housing forming a generally circular wall and blade sectors arranged along the wall. The housing includes several parts connected to each other by longitudinal flanges. Platforms with no fixing screws are located opposite the flanges. | 01-08-2015 |
20150030440 | FIRESHIELD FASTENER HOOD - A fireshield fastener hood and method of bonding a cover to a substrate therefor. | 01-29-2015 |
20150063993 | TURBO-MOLECULAR PUMP - A turbo-molecular pump comprises: a case having a suction port and a flange; a rotor assembly housed inside the case, the rotor assembly having a shaft and a rotor integrated with the shaft with a fastening bolt, the rotor having a plurality of rotor blades formed thereon; a plurality of stator blades housed inside the case and arranged to face the rotor blades; and a plurality of spacers stacked along a peripheral surface of the case, the spacer fixing the stator blades. An anti-corrosion treatment is applied to a gas contacting section in a component that is provided on an evacuation upstream side with respect to an evacuation downstream side end of the first rotor blade from the evacuation upstream side and made of an alloy containing Fe or Cr. | 03-05-2015 |
20150078891 | Hoop Tow Modification for a Fabric Preform for a Composite Component - A method of forming a fabric preform for a composite component from a fabric having a plurality of hoop tows is disclosed. One end of the fabric is received on the form such that the hoop tows of the fabric extend in a direction generally perpendicular to a central axis of the form. The fabric is wrapped around the form and at least some of the hoop tows are separated into hoop tow segments while the fabric is under a tension to enable a space to develop between ends of adjacent hoop tow segments along the length of the hoop tow. This separation of adjacent hoop tow segments accommodates increased deformation of the fabric during formation of the fabric preform while still maintaining a presence of hoop tow segments in at least portions of the fabric. | 03-19-2015 |
20150093239 | TURBOCHARGER BEARING HOUSING - There is provided a turbocharger bearing housing which is capable of reducing the weight thereof. A bearing housing of a turbocharger contains a shaft connecting a turbine and a compressor, and turnably supports the shaft. The bearing housing of the turbocharger is divided into a turbine-side housing disposed at a turbine side and a compressor-side housing disposed at a compressor side. The compressor-side housing is formed of an aluminum-based material. | 04-02-2015 |
20150098810 | HYBRID INNER FIXED STRUCTURE WITH METALLIC AND COMPOSITE CONSTRUCTION - Aspects of the disclosure are directed to a system for an aircraft comprising: a titanium bottle section that includes at least two sections configured to house an engine, and at least one bifurcation panel coupled to the bottle section, wherein the at least one bifurcation panel includes a material that is different from titanium. | 04-09-2015 |
20150104299 | TURBINE ENGINE VANE WITH ASYMMETRICAL PROFILE - The invention relates to a turbine engine vane comprising a main body made of composite material, a leading edge, a trailing edge, and at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, the vane being characterized in that the profile of the junction surface portion of the structural reinforcement has a camber less than 30%. | 04-16-2015 |
20150118036 | FAN CASE FOR AIRCRAFT ENGINE - An annular fan case which covers an outer periphery of a fan in an aircraft engine includes: a case body including a first composite material containing a fiber and a resin; and a containment section including a second composite material containing a fiber and a resin, the containment section being formed on an outer periphery of the case body. A resin content of the containment section is set to be lower than the resin content of the case body. | 04-30-2015 |
20150125281 | BRAZE ALLOY COMPOSITIONS AND BRAZING METHODS FOR SUPERALLOYS - A multi-component braze filler alloy comprising at least 70% by weight MarM509A superalloy with the remainder MarM509B superalloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. It is shown that generally higher braze temperatures lead to improved results including the possibility of re-welding such a brazed component, resulting in a re-repaired brazed component capable of continued commercial service. | 05-07-2015 |
20150125282 | BRAZE ALLOY COMPOSITIONS AND BRAZING METHODS FOR SUPERALLOYS - A multi-component braze filler alloy comprising 60-70% by weight CM247 superalloy and BRB braze alloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. The substrate/braze interface may be subsequently weld-repaired without de-melting and migrating the braze alloy from the interface. The weld zone and surrounding area are solidification crack resistant. After the alloy composition is brazed to the base substrate the component may be returned to service. Thereafter the component remains repairable by welding or re-brazing, if needed to correct future in-service defects. | 05-07-2015 |
20150125283 | FAN SALT-FOG-RESISTANT STRUCTURE AND FAN FRAME THEREOF - A fan salt-fog-resistant structure and a fan frame thereof. The fan salt-fog-resistant structure includes a base seat having a bearing cup and at least one flow guide body. Multiple connection bodies outward extend from the base seat. The flow guide body is disposed at a junction between the base seat and the connection bodies. The fan frame includes a main body having a first open side and a second open side and a flow passage defined therebetween. One end of the connection body is connected with the second open side. When airflow entraining moisture and salt fog flows through the junction between the base seat and the connection bodies, the flow guide body serves to guide the airflow and prevent the airflow from forming eddy, whereby the salt fog entrained by the airflow will not crystallize to form sediments at the junction between the base seat and the connection bodies. | 05-07-2015 |
20150132118 | COUPLING PART STRUCTURE FOR VANE AND JET ENGINE INCLUDING THE SAME - A coupling support member including a pair of divided pieces is placed in a coupling part between a vane proximal end portion of a guide vane and an attachment flange, and the pair of divided pieces are joined to the vane proximal end portion from both the sides in the vane thickness direction. A groove is formed in one end portion joint surface of the coupling support member, a linear protrusion is formed on the other end portion joint surface, the vane proximal end portion is formed into a concavo-convex shape, a linear protrusion that is engaged with the groove which is formed in the end portion joint surface is formed on a joint surface to the one end portion joint surface, a groove that is engaged with the linear protrusion formed on the end portion joint surface is formed in the joint surface to the other end portion joint surface. The vane proximal end portion is held between the pair of divided pieces of the coupling support member, by the fastening force that is applied to the coupling support member from both the sides in the vane thickness direction. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine. | 05-14-2015 |
20150147166 | FAN MODULE - A fan module, applied to a server including a first joint portion, includes a fan body, a first metal casing, a second metal casing and a plastic handle. The fan body includes an outlet surface, an inlet surface opposite to the outer surface, a first lateral surface and a second lateral surface. The first and second lateral surfaces are located between the outlet surface and the inlet surface. The first metal casing includes an air-through wall located on the outlet surface or the inlet surface, a first lateral wall connected to the air-through wall and mounted on the first lateral surface, and a metal handle connected to the first lateral wall. The second metal casing includes a second lateral wall mounted on the second lateral surface. The plastic handle, mounted on the second lateral wall, includes a second joint portion, for being engaged with the first joint portion. | 05-28-2015 |
20150292341 | VANE CARRIER FOR A COMPRESSOR OR A TURBINE SECTION OF AN AXIAL TURBO MACHINE - A vane carrier is provided for a compressor or a turbine section of an axial turbo machine, especially one of a gas turbine, steam turbine, compressor, expander, comprises least a first and second functional means. The first functional means is a cylinder made of a material with a coefficient of thermal expansion (CTE) below 1.3×10 | 10-15-2015 |
20150292361 | Composite Casing For A Compressor Of An Axial-Flow Turbomachine - A composite external casing for a compressor of an axial-flow turbomachine, the casing comprising a generally circular wall having a matrix and a woven fibrous reinforcement. The latter is formed by a stack of fibrous plies having fibers woven according to a weft positioned in the axis of the circular wall, and a warp positioned around the circumference of the wall. The stack of plies comprising, depending on thickness, two external layers and one central layer. The layers include differences in the proportions between the weft fibers and the warp fibers. In the external layers the warp fibers make up the majority. In the central layer the weft fibers make up the majority. The stack exhibits interlayers inserted between the central layer and each external layer. The plies corresponding to the interlayers exhibit fibers woven at +45° and −45° in relation to the axis of rotation of the turbomachine. | 10-15-2015 |
20150299862 | MANUFACTURING METHOD OF ROTATING MACHINE, PLATING METHOD OF ROTATING MACHINE, AND ROTATING MACHINE - A manufacturing method of a rotating machine ( | 10-22-2015 |
20150300367 | CENTRIFUGAL FAN - A centrifugal fan is provided. The centrifugal fan includes a main plate connected to a rotational shaft of a motor, a shroud having a suction opening, through which air is introduced, a plurality of blades arranged between the main plate and the shroud, and a rim formed by bending an outer circumference of at least one of the main plate or the shroud in a longitudinal direction of the rotational shaft, the rim portion having an inclination. | 10-22-2015 |
20150308277 | Blade Retaining Ring for an Internal Shroud of an Axial-Flow Turbomachine Compressor - The present application relates to a stator of a low-pressure compressor of an axial-flow turbomachine. The stator includes an annular row of stator blades including radial extremities which pass through the openings of an internal shroud, and which include radial retaining slots having tapers formed by hooks. The stator also includes a ring for retaining the blades on the internal shroud. The ring is curved circumferentially in order to be inserted into a plurality of retaining slots and exhibits the form of a strip having an arched transversal profile which is in abutment against the tapers, in such a way as to maintain the ring in the interior of the slots. The shroud includes an annular layer of abradable material made from silicone, which encloses the ring in such a way as to block the curvature of the arched profile of the ring in order to prevent it from disengaging from the tapers of the slots. | 10-29-2015 |
20150322815 | CAST STEEL FRAME FOR GAS TURBINE ENGINE - A gas turbine engine comprises a first turbine module, a second turbine module, and a frame interconnecting the first turbine module with the second turbine module. The frame includes a plurality of circumferentially distributed struts extending radially between an inner hub and an outer case, and is formed from a single steel sand casting. | 11-12-2015 |
20150322963 | CASING AND BLOWER - A casing includes a first plate made of a metal, a support made of a resin, and a second plate fixed to the support. The first plate includes a flat plate portion, a through hole passing through the flat plate portion, and a claw portion extending upward from an edge of the through hole. A portion of the support is located in the through hole. The support covers a portion of the claw portion such that the support is prevented from turning and from coming off in an upward direction. The claw portion is defined by a portion of the first plate extending along a longest line segment inside the through hole in a plan view being bent upward from the flat plate portion. This enables the claw portion to have a great length even in a small area of the first plate to securely fix the support to the first plate. | 11-12-2015 |
20150330405 | TURBOCHARGER BEARING HOUSING WITH CAST- IN PIPES - Conventionally, turbocharger bearing housings are cast, and then oil passageways are drilled or bored into the casting. As a result, bores are limited to straight lines extending from drill access points. Greater design flexibility is provided by pre-staging in a mold a collection of metal pipes which will define one or more of oil, air and water galleries, and then casting a bearing housing around the pipes. This provides almost unlimited freedom in shaping and locating the oil bores and other features. | 11-19-2015 |
20150337668 | Blade Rub Material - One aspect of the disclosure involves a rub material comprising a polymeric matrix and polymer micro-balloon filler in the matrix. In one or more embodiments of any of the foregoing embodiments, the matrix comprises a silicone. In one or more embodiments of any of the foregoing embodiments, the rub material is at least I.0 mm thick. In one or more embodiments of any of the foregoing embodiments, the silicone is selected from the group consisting of dimethyl- and fluoro-silicone rubbers and their copolymers. In one or more embodiments of any of the foregoing embodiments, the micro-balloons at least locally have a concentration of 5-50% by volume. | 11-26-2015 |
20150345502 | MOTOR CASING FOR PUMPS, PARTICULARLY CENTRIFUGAL PUMPS AND PERIPHERAL CENTRIFUGAL PUMPS - A motor casing for pumps, particularly centrifugal pumps and peripheral centrifugal pumps, containing a motor associated with the hydraulic part, provided with at least one impeller, by means of a rotation transmission shaft, the motor casing having at least one surface that is struck by pumping liquid that arrives from the hydraulic part and is provided with an oxidation-resistant coating. | 12-03-2015 |
20150354377 | MONOBLOC BLADE PREFORM AND MODULE FOR A TURBO MACHINE INTERMEDIATE CASING - A fiber preform for a vane module of an intermediate casing of a turbine engine, the preform being obtained by three-dimensional weaving. The preform includes first longitudinal segment presenting opposite first and second ends and suitable for forming a first vane; a second longitudinal segment presenting first and second opposite ends and suitable for forming a second vane; and a first transverse segment connecting together the first and second longitudinal segments by their first ends, and suitable for forming a first transverse vane portion such as a flange or a platform. | 12-10-2015 |
20150354411 | TURBINE EXHAUST CASE MULTI-PIECE FRAME - A turbine exhaust case (28) comprises a one-piece fairing (120) defining an air-flow path through the turbine exhaust case, and a multi-piece frame (100). The multi-piece frame is disposed through and around the one-piece vane fairing to support a bearing load, and comprises an inner ring (104), an outer ring (102), a plurality of covers (110), and a plurality of radial struts (106). The outer ring is disposed concentrically outward of the inner ring, and has hollow bosses (114) with strut apertures (SA) at vane locations. The covers are secured to the hollow bosses. The radial struts pass through the one-piece vane fairing and through apertures in the outer angled ring, and are radially fastened to the inner ring and the flat caps. | 12-10-2015 |
20150354413 | TURBINE EXHAUST CASE MULTI-PIECE FRAME - A turbine exhaust case ( | 12-10-2015 |
20150369066 | GAS TURBINE ENGINE WITH THERMOPLASTIC FOR SMOOTHING AERODYNAMIC SURFACES - A gas turbine engine has a surface configured for a gas flow path. The surface has at least one structural member defining a gap. A thermoplastic is deposited into the gap to smooth the surface, whereby the surface is aerodynamically and mechanically smoothly continuous over the gap area. A method is also disclosed. | 12-24-2015 |
20150377038 | CORE POSITIONING - A method locates and maintains a core in fixed space relationship within the interior of shell mould. The method provides at least one pin extending into the core with at least one axial end of pin protruding from the core. A wax pattern having an outer surface is formed by encasing the core and at least one protruding axial end of pin in wax such that at least one protruding axial end of the pin terminates at the outer surface of wax pattern. A shell mould is formed around the wax pattern such that, upon removal of the wax pattern, and in subsequent casting process for production of hollow metal components, at least one protruding axial end of the pin abuts the shell mould thus fixing the pin and maintaining position of the core relative to the mould. The protruding axial end of the pin has an enlarged head. | 12-31-2015 |
20150377045 | STRESS MITIGATION FEATURE FOR COMPOSITE AIRFOIL LEADING EDGE - A vane assembly within a mid-turbine frame of a gas turbine engine includes an airfoil that extends between an outer platform and an inner platform. The airfoil includes an outer wall defining a leading edge of a first radius. An inner wall of the airfoil defines an inner cavity including a forward portion proximate the leading edge defining a second radius different than the first radius. | 12-31-2015 |
20150377046 | GAS TURBINE ENGINE COMPOSITE AIRFOIL TRAILING EDGE - An airfoil for a gas turbine engine includes first pressure and suction side layers forming a cavity and terminating in ends near a trailing edge. The first and second suction side layers are constructed from a composite material. A bridge is wrapped about the ends. | 12-31-2015 |
20150377067 | MID TURBINE FRAME (MTF) FOR A GAS TURBINE ENGINE - A mid-turbine frame for a gas turbine engine includes a CMC outer ring, a CMC inner ring, and a multiple of CMC airfoils between the CMC outer ring and the CMC inner ring. Each of the CMC airfoils includes at least one hollow tube and a shell of a multiple of CMC plies surrounding the hollow tube. The hollow tube reinforces the shell. A spring biased tie-rod assembly is mounted through at least one of the multiple of CMC airfoils. | 12-31-2015 |
20160003072 | GAS TURBINE ENGINE THIN WALL COMPOSITE VANE AIRFOIL - An airfoil for a gas turbine engine has a first layer forming a cavity having transitioning from a first thickness to a second thickness through a ply drop region. A second layer is secured to the first layer. | 01-07-2016 |
20160003073 | GUIDE VANE ASSEMBLY VANE BOX OF AN AXIAL TURBINE ENGINE COMPRESSOR - The invention relates to an angular sector of a bladed stator of a low-pressure compressor of an axial turbine engine. The sector comprises an outer shroud and an inner shroud in the form of circular arcs intended to be mounted in a concentric manner on the outer casing of the turbine engine compressor. The sector likewise comprises a row of stator vanes extending radially and anchored in the shrouds in such a manner as to form a bladed box. The vanes of the box comprise anchoring lugs at their outer ends, the lugs being disposed in the thickness of the outer shroud. The inner shroud comprises stubs for anchoring vanes. | 01-07-2016 |
20160003104 | GAS TURBINE ENGINE ATTACHMENT STRUCTURE AND METHOD THEREFOR - An attachment structure for a gas turbine engine includes a frame that has a first annular case. A second annular case extends around the frame. The first annular case and the second annular case include a plurality of interlocks. Each of the interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second case. The first member is received in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case. | 01-07-2016 |
20160010468 | COMPOSITE AIRFOIL METAL LEADING EDGE ASSEMBLY | 01-14-2016 |
20160012178 | METHOD OF DESIGNING A COMMON PREFORM FOR PROVIDING PREFORMS FOR TURBINE ENGINE OUTLET GUIDE VANES OF DIFFERENT GEOMETRICAL PROFILES AND MADE OUT OF COMPOSITE MATERIAL | 01-14-2016 |
20160017723 | Co-Formed Element with Low Conductivity Layer - A co-formed element includes a core structure which has a root portion and is formed from a high thermal conductivity ceramic matrix composite material, and a low thermal conductivity layer co-formed with the core structure and surrounding the root portion of the core structure. | 01-21-2016 |
20160017733 | MULTIPLE COATING CONFIGURATION - An article includes a body that has a coating thereon. The coating has a first portion disposed on a first section of the body and a second portion disposed on a second, different section of the body. The first portion has a first microstructure and the second portion has a second, different microstructure. | 01-21-2016 |
20160017753 | BOLT ATTACHMENT TO COMPOSITE FAN CASE - A fan case includes a composite fan case body including an outer surface and at least one attachment tool attached to the outer surface of the fan case body. The attachment tool includes a boss that has at least one fastener opening with a threaded insert. A channel extends from at least one interior cavity of the attachment tool through an outer wall of the attachment tool. | 01-21-2016 |
20160024943 | STRUCTURAL GUIDE VANE LEADING EDGE - A structural guide vane for use in a gas turbine engine has a leading edge section, a trailing edge, a pressure surface and a suction surface. An erosion coating such as polyurethane resin is on the pressure surface and the suction surface. The leading edge of the vane is without the erosion coating and is bare metal. The vane is formed to include a plurality of pockets and bond shelves in the pressure surface side, and an epoxy bond line on the bond shelves holding a cover plate protected by the erosion coating. | 01-28-2016 |
20160024955 | Maxmet Composites for Turbine Engine Component Tips - A turbine engine system includes a turbine engine component having an airfoil portion and a tip, which turbine engine component having a MAXMET composite bonded to the tip. The MAXMET composite has MAX phases in a metal matrix. | 01-28-2016 |
20160024969 | COMPOSITE FLANGE FROM BRAIDED PREFORM - A preform sheet for a composite component comprises a body section and a flange section. The preform body section includes a plurality of axial tows braided with at least a plurality of first bias tows and a plurality of second bias tows. The preform flange section includes a first braided flange layer and a second braided flange layer. The first braided flange layer is defined by the first and second braided bias tows of the preform body section extending into the flange section. Neither the first nor second braided flange layers have axial tows. | 01-28-2016 |
20160032744 | SELECTIVE COATING REMOVAL OR MASKING FOR GROUND PATH - A device for providing a grounding path between an outer surface of a gas turbine aircraft engine and an inner surface of a gas turbine aircraft engine uses a structural guide vane (SGV) with a nonconductive coating on the surface. Bolts are put in bolt holes that have a bolt receiving cavity without the nonconductive coating. A washer and bolt are used so that attachment of the SGV to a surface provides a ground path from the SGV through the bolt, washer and nut for electrical engagement with a surface to which the bolt attaches the SGV. | 02-04-2016 |
20160032774 | Cost Effective Manufacturing Method for GSAC Incorporating a Stamped Preform - A process for manufacturing a preformed sheet having geometric surface features for a geometrically segmented abradable ceramic thermal barrier coating on a turbine engine component, the process comprising the steps of providing a preformed sheet material. The process includes forming a partially of geometric surface features in the sheet material. The process includes joining the sheet material to a substrate of the turbine engine component. The process includes disposing a thermally insulating topcoat over the geometric surface features and forming segmented portions that are separated by faults extending through the thermally insulating topcoat from the geometric surface features. | 02-04-2016 |
20160032776 | REINFORCED COMPOSITE CASE - A composite assembly comprises a first composite wall, a second composite wall spaced radially inward from the first outer wall, and a composite reinforcement ring attached to an outer surface of the second composite wall. The composite reinforcement ring includes at least one sidewall having an accessory mounting port formed therethrough. | 02-04-2016 |
20160053622 | STATOR VANE ARRANGEMENT FOR A TURBINE ENGINE - A stator vane arrangement for a turbine engine includes a first vane platform, a second vane platform and a plurality of stator vanes extending radially between the first and the second vane platforms. The first and the second vane platforms extend circumferentially around an axis, and the first vane platform includes an aperture. The stator vanes are arranged circumferentially around the axis, and include a first stator vane that extends radially into the aperture and is fastened to the first vane platform. | 02-25-2016 |
20160069216 | SHROUD DEVICE OF A JET ENGINE - A shroud device of a jet engine, including a radially internal shroud appliance and a radially external shroud appliance. The internal shroud appliance is embodied with a radially internal ring-shaped shroud part and a radially external ring-shaped shroud part. The internal shroud appliance includes multiple blades that extend substantially in the radial direction between the internal shroud part and the external shroud part. The radially external shroud appliance is embodied with a radially internal ring-shaped shroud part and a radially external ring-shaped shroud part. The external shroud appliance includes multiple blades that extend substantially in the radial direction between the internal shroud part and the external shroud part. The internal shroud appliance is embodied as a first one-piece cast structural component and the external shroud appliance is embodied as a second one-piece cast structural component. | 03-10-2016 |
20160069355 | PANELS OF A FAN OF A GAS TURBINE - An aircraft gas turbine with a fan disk on which are fastened fan blades spread over the circumference and forming an intermediate space with one another, with a sealing disk arranged at the rear of the fan disk and with an inlet cone mounted at the front of the fan disk, as well as with filler elements arranged in the intermediate spaces, where the sealing disk has an annular groove and where the filler elements are at the rear inserted into the annular groove and at the front held underneath a rim area of the inlet cone, characterized in that the filler elements are designed as bending beams and that on the radially inner side of the filler element at least one rib-like reinforcing area is provided, extending in the axial direction and longitudinally to the filler element. | 03-10-2016 |
20160075063 | COMPOSITE CASING FOR AXIAL TURBOMACHINE LOW-PRESSURE COMPRESSOR - The invention relates to a method for manufacturing a composite casing for an axial turbomachine low-pressure compressor. The casing comprises a circular wall and a fixing flange which with the wall forms a sharp-edged corner. The method comprises the steps of: supplying a mould with a corner configured to form the edge corner of the casing; placing a filled thermoplastic resin profile section along the corner; placing a fibrous reinforcement in the mould to hug the profile section; closing the injection mould; polymerizing a resin injected into the mould and demoulding the casing. The invention also relates to a composite casing with an annular wall and a flange at one end of the wall forming a sharp-edged corner on the inside of the casing. The casing is reinforced by a fibrous perform and the edge corner is reinforced with short fibers with a mean length of less than 5.00 mm. | 03-17-2016 |
20160090867 | APPARATUS FOR MOUNTING A COMPONENT IN A GAS TURBINE ENGINE - Apparatus for mounting a component in a gas turbine engine, the apparatus comprising: a casing for a gas turbine engine, the casing including a flange; a first connector to connect a component of the gas turbine engine to the casing at a first location adjacent to the flange; and a second connector to connect the component of the gas turbine engine to the casing at a second location adjacent to the flange. | 03-31-2016 |
20160096288 | TOOLING PRODUCTION METHOD - A method is provided of producing a tooling to be used for manufacturing a rigid panel formed of polymer matrix composite material. The panel is for attachment to a gas turbine engine and has a curved shape which allows the panel to be wrapped around at least a part of a circumference of the engine. The panel has plural electrical conductors and/or fluid passages embedded therein. The tooling is either a mould against which the polymer matrix composite material can be moulded to manufacture the panel, or a pattern from which such a mould can be formed. The method includes: providing a plurality of separate tooling segments, each of which corresponds to a respective region of the curved shape of the panel; and joining the tooling segments together to produce the tooling. | 04-07-2016 |
20160102576 | BRAZE MATERIALS AND METHOD FOR JOINING OF CERAMIC MATRIX COMPOSITES - A gas turbine engine includes at least two components. The first component is coupled to the second component by a melt alloy. | 04-14-2016 |
20160108747 | STATOR VANE STRUCTURE AND TURBOFAN JET ENGINE USING THE SAME - A distal end portion and a proximal end portion of a guide vane formed from a composite material are respectively supported by connecting support bodies formed from a metal, and the connecting support bodies of the distal end portion and the proximal end portion are connected by a conductive wire while the conductive wire is passed through a space between a leading edge surface of the guide vane and a sheath. In a turbofan jet engine, a lightning current due to a lightning strike can be fended off while a controlling function of a stator vane formed from a composite material is ensured, and an inspection is also easy. | 04-21-2016 |
20160115820 | HOLLOW METAL OBJECTS AND METHODS FOR MAKING SAME - A method of making a hollow metal component comprising the steps of providing at least one core comprising a first side and a reverse side; utilizing a first metal spray process to apply at least one metal or metal alloy to the first side of the core, resulting in a partially-formed structure comprising a first side and a reverse side; and utilizing a second metal spray process to apply at least one metal or metal alloy to the reverse sides of the partially-formed structure and the core, resulting in a rough structure. A hollow metal component comprising a first side having interior and exterior surfaces, a reverse side having interior and exterior surfaces, the interior surfaces of the first side and the reverse side defining at least one cavity. The component is integrally formed and has regions comprising relatively different material compositions, the regions having gradual transitions of materials therebetween. | 04-28-2016 |
20160115822 | Lattice Type Blade Of An Axial Turbine Engine Compressor - The invention relates to a blade of a low-pressure compressor of an axial turbine engine. The blade comprises a vane in which a cavity is formed. The vane has a leading edge and a trailing edge, an intrados surface and an extrados surface which extend from the leading edge to the trailing edge, an outer casing which forms the intrados surface and the extrados surface and which delimits the cavity. The blade further comprises closed foam, such as a polymethacrylic foam, which blocks the cavity in order to isolate it from the environment of the blade. The blade further has a three-dimensional lattice which is formed in the cavity and which is integral with the vane of the blade. This barrier protects from chemical attacks and the introduction of impurities. The invention also relates to a production method for a hollow turbine engine blade which is filled with foam. | 04-28-2016 |
20160123163 | VANE ASSEMBLY FOR A GAS TURBINE ENGINE - A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil. | 05-05-2016 |
20160123164 | VANE ASSEMBLY FOR A GAS TURBINE ENGINE - A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A reinforcement spar made from a metallic material extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil. | 05-05-2016 |
20160130952 | Vibration-Damped Composite Airfoils and Manufacture Methods - A turbine engine component ( | 05-12-2016 |
20160130978 | STAINLESS STEEL ALLOYS, TURBOCHARGER TURBINE HOUSINGS FORMED FROM THE STAINLESS STEEL ALLOYS, AND METHODS FOR MANUFACTURING THE SAME - Disclosed is an austenitic stainless steel alloy that includes, by weight, about 22% to about 28% chromium, about 3.5% to about 6.5% nickel, about 1% to about 6% manganese, about 0.5% to about 2.5% silicon, about 0.3% to about 0.6% carbon, about 0.2% to about 0.8% nitrogen, and a balance of iron. Molybdenum, niobium, and tungsten are excluded. The alloy is suitable for use in turbocharger turbine housing applications for temperature up to about 980° C. | 05-12-2016 |
20160130979 | TURBINE HOUSING FOR AN EXHAUST GAS TURBOCHARGER - The invention relates to a turbine housing ( | 05-12-2016 |
20160138423 | TITANIUM-ALUMINIDE COMPONENTS - The present disclosure relates to a hot section gas turbine engine component assembly and a method for forming such. | 05-19-2016 |
20160146052 | FORGED CAST FORGED OUTER CASE FOR A GAS TURBINE ENGINE - A case for a gas turbine engine includes a cast case section cast case section configured to be welded between a forward case section and an aft case section. | 05-26-2016 |
20160153295 | COMPOSITE VANE FOR A TURBINE ENGINE | 06-02-2016 |
20160160658 | COMPOSITE AIRFOIL - An airfoil includes a core with a first Young's Modulus; and an outer section at least partially surrounding the core with a second Young's Modulus, wherein the first Young's Modulus is higher than the second Young's Modulus. | 06-09-2016 |
20160160659 | COMPOSITE VANE - A composite vane body formed of a composite material of a thermosetting resin or a thermoplastic resin, and reinforced fibers, and a metal sheath that is bonded to a leading edge section of the composite vane body via a soft adhesive to cover the leading edge section are included, and an adhesive filling section in which the soft adhesive is filled, a plurality of leading edge side contact sections that come into contact with a curved section corresponding to a leading edge of the metal sheath, and a plurality of protrusions that come into contact with a planar section corresponding to a vane surface of the metal sheath, with at least a same height as a thickness of a layer of a requisite amount of the soft adhesive filled in the adhesive filling section are formed in the leading edge section of the composite vane body. Attachment of the metal sheath to the leading edge section can be performed easily with high precision. | 06-09-2016 |
20160160680 | COMPRESSED CHOPPED FIBER COMPOSITE STRUCTURAL GUIDE VANE - The present disclosure relates generally to the field of guide vanes for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber structural guide vane for a gas turbine engine. | 06-09-2016 |
20160160800 | COMBINED FAN BYPASS COMPONENTS WITH REMOVABLE FRONT FRAME STRUCTURE FOR USE IN A TURBOFAN ENGINE AND METHOD FOR MAKING SAME - A system and method is provided that combines fan bypass components and minimizes assembly interfaces in a turbofan engine. The system and method provide a front frame structure of reduced weight that slidably installs/removes from within the combined fan bypass components. | 06-09-2016 |
20160160869 | PLATED POLYMER COMPRESSOR - Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure. | 06-09-2016 |
20160169013 | Gas Turbine Engine Component with Abrasive Surface Formed by Electrical Discharge Machining | 06-16-2016 |
20160169033 | APPARATUS AND SYSTEM FOR CERAMIC MATRIX COMPOSITE ATTACHMENT | 06-16-2016 |
20160169045 | TURBINE ENGINE CASING AND MANUFACTURING METHOD | 06-16-2016 |
20160169046 | STIFFENING RIB | 06-16-2016 |
20160169226 | LIQUID RING FLUID FLOW MACHINE | 06-16-2016 |
20160177428 | STAINLESS STEEL ALLOYS, TURBOCHARGER TURBINE HOUSINGS FORMED FROM THE STAINLESS STEEL ALLOYS, AND METHODS FOR MANUFACTURING THE SAME | 06-23-2016 |
20160177759 | MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE NOZZLE | 06-23-2016 |
20160177969 | COMPRESSOR BLADE OF A GAS TURBINE | 06-23-2016 |
20160186579 | HYBRID GAMMA TiAl ALLOY COMPONENT - A hybrid component for a turbine engine having a casing includes a first part of a gamma TiAl intermetallic alloy and a second part of a material of at least one of nickel, a nickel base, a cobalt base, an iron base superalloy or mixtures thereof. The second part is coupled to and configured to attach the first part to the casing of the engine. The first and second parts are attached to each other by transient liquid phase (TLP) bonding. | 06-30-2016 |
20160186612 | CASING RING ASSEMBLY WITH FLOWPATH CONDUCTION CUT - A casing assembly for a gas turbine engine having a centerline axis, the casing apparatus includes: a metallic inner ring defining an annular flowpath surface; a metallic outer ring positioned in axial alignment with and radially outward of the inner ring; and a conduction cut structure disposed between the inner and outer rings. | 06-30-2016 |
20160194091 | ELECTRIC CONDUCTION STRUCTURE FOR JET ENGINE | 07-07-2016 |
20160195063 | METHOD FOR PRODUCING A COMPOSITE MOLDED PART, COMPOSITE MOLDED PART, SANDWICH COMPONENT, ROTOR BLADE ELEMENT, AND WIND TURBINE | 07-07-2016 |
20160201478 | BRAIDED BLADES AND VANES HAVING DOVETAIL ROOTS | 07-14-2016 |
20160201480 | AIRFOIL WITH AN INTEGRALLY STIFFENED COMPOSITE COVER | 07-14-2016 |
20160201505 | Fan Cases and Manufacture Methods | 07-14-2016 |
20170234160 | AIRCRAFT ENGINE WITH AN IMPACT PANEL | 08-17-2017 |
20170234162 | STEAM TURBINE INNER CASING COMPONENT AND REPAIR METHOD THEREFOR | 08-17-2017 |
20190145263 | TURBINE COMPONENTS WITH NEGATIVE CTE FEATURES | 05-16-2019 |
20220134690 | REPAIR OR RESUMPTION OF MANUFACTURE OF A COMPOSITE MATERIAL PART WITH FIBROUS THREE-DIMENSIONAL WOVEN REINFORCEMENT - A method for repairing a part made of composite material includes producing a recessed section by removing the composite material at a damaged area, producing grooves extending on the two faces of the part from edges of the recessed section, producing orifices in the part opening out into the grooves, tree-dimensional weaving of a filling part fiber preforms including a central section having a shape corresponding to the shape of the recessed section and fiber bundles extending from the central section, placing the filling preforms respectively on either face of the part with the fiber bundles in the grooves on the faces of the part and in the orifices such that the fiber bundles open out into the grooves present on the opposite face of the part, impregnating the filling fiber preforms with a precursor resin of a matrix, transforming the resin into a matrix to obtain a filling part. | 05-05-2022 |