UNITED TECHNOLOGIES CORPORATION Patent applications |
Patent application number | Title | Published |
20160138421 | NONLINEAR ROLLING BEARING RADIAL SUPPORT STIFFNESS - A bearing support assembly includes a squirrel cage defining a longitudinal axis and having a cylindrical portion defining a bearing seat. The squirrel cage is configured and adapted to provide a first level of radial support stiffness between a housing and a bearing seated in the bearing seat. A damper sleeve is operatively coupled to the cylindrical portion of the squirrel cage through a fluid film to dampen relative radial motion between the damper sleeve and the squirrel cage. A radial spring component is operatively connected to a side of the damper sleeve radially opposite the cylindrical portion of the squirrel cage to provide a second level of radial support stiffness. | 05-19-2016 |
20160130977 | TURBINE ROTOR SEGMENTED SIDEPLATES WITH ANTI-ROTATION - A segmented sideplate for use in a gas turbine engine is described. The segmented sideplate includes a first plate having a first circumferential edge configured to interface with a complementary circumferential edge. The segmented sideplate also includes a second plate having a second circumferential edge configured to interface with the first circumferential edge. | 05-12-2016 |
20160130952 | Vibration-Damped Composite Airfoils and Manufacture Methods - A turbine engine component ( | 05-12-2016 |
20160123187 | HEATSHIELD ASSEMBLY WITH DOUBLE LAP JOINT FOR A GAS TURBINE ENGINE - A heat shield assembly for a gas turbine engine includes a first heat shield segment defined about an axis and a second heat shield segment defined about the axis. A double circumferential lap joint is defined between the first heat shield segment and the second heat shield segment. | 05-05-2016 |
20160123184 | COMBINED FAN CASE ICE LINER AND REAR LINER - A jet engine fan case is disclosed. The fan case may comprise an ice liner section and a rear liner section, wherein the ice liner section and the rear liner section are constructed from a constructed from a single, integral material. The ice liner section may comprise fiberglass and the rear liner section comprises fiberglass, such that the combined liner comprises a single piece. The combined liner may comprise a plurality of segments in the range of one segment to nine segments. The ice liner section may comprise a first cross-sectional profile and the rear liner section may comprise a second cross-sectional profile. The ice liner section may comprise a first cross-sectional profile and the rear liner section may comprise a second cross-sectional profile that is less than the first cross-sectional profile. The combined liner may comprise an uninterrupted aerodynamic surface. | 05-05-2016 |
20160123177 | VANE ARM WITH INCLINED RETENTION SLOT - The present disclosure includes vane assemblies having a vane lever arm with an inclined profile. The inclined profile may engage with a complementary end of a vane shaft to locate, retain, and prevent rotation of the vane shaft and vane. | 05-05-2016 |
20160122005 | EMBEDDED ENGINES IN HYBRID BLENDED WING BODY - A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer. | 05-05-2016 |
20160109128 | GAS TURBINE ENGINE WAVE GEOMETRY COMBUSTOR LINER PANEL - A panel for a combustor of a gas turbine engine includes a cold side defining at least one convex portion and at least one concave portion. The concave portion is in communication with a passage. A method of operating a combustor section of a gas turbine engine includes: directing an impingement flow toward a multiple of peaks on a cold side of a panel; directing the impingement flow from the multiple of peaks toward a multiple of troughs with a multiple of entrances on the cold side of the panel; and directing the impingement flow through the multiple of entrances and a respective multiple of effusion passages through the panel. | 04-21-2016 |
20160109025 | SEAL RING - A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe. | 04-21-2016 |
20160108819 | Fuel/Oil Manifold - A single, unitary fuel/oil manifold for a gas turbine engine is provided which comprises one or more interfaces for mounting various fuel system and lubricating system components directly to the fuel/oil manifold. The fuel/oil manifold also defines fluid passages for transferring fuel or lubricant from one component to another component. Packing numerous fuel system and lubricating system components within the fuel/oil manifold reduces cost and weight and simplifies maintenance. | 04-21-2016 |
20160108812 | CONDUIT FOR GUIDING LOW PRESSURE COMPRESSOR INNER DIAMETER SHROUD MOTION - Conduits for guiding the motion of an inner diameter shroud of a low pressure compressor of a gas turbine engine are disclosed. The inner diameter shroud has at least three slots formed in one or more radially inwardly extending flanges. Each of the conduits are configured to assemble with a respective one of the at least three slots. Each conduit comprises a bushing having a first panel, and the first panel is capable of being inserted in a respective one of the slots of the inner diameter shroud. The conduit further comprises a bracket capable of being attached to a bearing support of a fan intermediate case of the gas turbine engine. The bushing is capable of being attached to the bracket. A contact between the first panel and the at least one slot of the inner diameter shroud restricts a circumferential rotation of the inner diameter shroud with respect to a central axis of the gas turbine engine when the first panel is inserted in the at least one slot, but allows a radial motion of the inner diameter shroud with respect to the central axis. | 04-21-2016 |
20160108808 | Turbofan Engine Bearing and Gearbox Arrangement - A turbofan engine ( | 04-21-2016 |
20160108739 | FILM HOLE WITH PROTRUDING FLOW ACCUMULATOR - A wall of a gas turbine engine is provided. The wall may comprise an external surface adjacent a gas path and an internal surface adjacent an internal flow path. A film hole may have an inlet at the internal surface and an outlet at the external surface. A flow accumulator adjacent the inlet may protrude from the internal surface. A method of making an engine component is also provided and comprises the step of forming a component wall comprising an accumulator on an internal surface and a film hole defined by the component wall. The film hole may include an opening adjacent the accumulator and defined by the internal surface. | 04-21-2016 |
20160102570 | NON-CONTACTING DYNAMIC SEAL - Non-contacting dynamic seals having wave springs are disclosed herein. A non-contacting dynamic seal may have a shoe coupled to an outer ring by an inner beam and an outer beam. A wave spring may be located between the inner beam and the outer beam, between the shoe and the inner beam, or between the outer beam and the outer ring. The wave spring may damp vibrations in the inner beam and the outer beam. | 04-14-2016 |
20160097327 | SYNCHRONIZED AIR MODULATING SYSTEM - A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door. | 04-07-2016 |
20160097294 | BRUSH SEAL PLATE - A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin. | 04-07-2016 |
20160090915 | INLET DOOR CONTROL FOR STARTUP OF GAS TURBINE ENGINE - A gas turbine engine inlet door control system includes an actuator, an engine controller and a door controller. The actuator opens and closes an inlet door of a gas turbine engine. The engine controller determines an intermediate door position based upon one or more engine start factors. The door controller operates the actuator to open the inlet door to the intermediate door position based on the one or more engine start factors. | 03-31-2016 |
20160084168 | Chemistry Based Methods of Manufacture for Maxmet Composite Powders - A method of manufacturing a gas turbine engine air seal comprising forming at least one MAX phase particle. The method includes coating the at least one MAX phase particle with a metallic shell. The method includes applying the at least one MAX phase metallic coated particle to a surface of a substrate of the air seal to form an abradable layer of a MAXMET composite abradable material from the at least on MAX phase metallic coated particle. | 03-24-2016 |
20160084167 | SELF-MODULATED COOLING ON TURBINE COMPONENTS - Systems and methods are disclosed herein for passively managing cooling air in a gas turbine engine. A cooling air supply line may supply cooling air to a component in the gas turbine engine. A metering coupon may have a negative coefficient of thermal expansion. The metering coupon may allow more airflow through the metering coupon and through the component in response to an increase in temperature. | 03-24-2016 |
20160084100 | SYSTEM AND APPARATUS FOR SEAL RETENTION AND PROTECTION - A sheath and seal assembly for protecting, containing and insulating a seal is provided. The seal may be installable within the sheath forming a seal-sheath assembly. The assembly may be capable of being installed in the hot section of a gas turbine. The sheath may be a woven, braided, and/or chain link structure. The sheath may be capable of allowing pressure to be conducted to a portion of the seal to load the seal against one or more portions of a housing. | 03-24-2016 |
20160083304 | ADDITIVE MANUFACTURING OF CERAMIC TURBINE COMPONENTS BY PARTIAL TRANSIENT LIQUID PHASE BONDING USING METAL BINDERS - A ceramic turbine component is formed by a process including mixing a ceramic powder with a metal binder powder mixture. The powder mixture is then formed into a turbine component that is subsequently densified by partial transient liquid phase sintering. In an embodiment, the turbine component may be formed by an additive manufacturing process such as selective laser sintering. | 03-24-2016 |
20160083303 | ADDITIVE MANUFACTURING OF CERAMIC TURBINE COMPONENTS BY TRANSIENT LIQUID PHASE BONDING USING METAL OR CERAMIC BINDERS - A ceramic turbine component is formed by a process including mixing a ceramic powder with an inorganic binder powder. The powder mixture is then formed into a turbine component that is subsequently densified by transient liquid phase sintering. In an embodiment, the turbine component may be formed by an additive manufacturing process such as selective laser sintering. | 03-24-2016 |
20160083101 | AIRCRAFT ENGINE CASE SHOCK MOUNT - The present disclosure relates to shock mounts for turbine engine components. A shock mount may be used to mount an accessory gearbox to an engine case. The shock mount may allow free thermal expansion, while providing damping and stiffness in response to vibrations. The shock mount may include a cylinder filled with fluid, and a piston telescopically moveable within the cylinder. The piston may be coupled to an orifice plate. The orifice plate may include orifices through which the fluid may flow in response to compression or extension of the shock mount. The interaction of the fluid and the orifice plate may resist rapid compression or extension of the shock mount while allowing relatively slow compression or extension of the shock mount. | 03-24-2016 |
20160076451 | FILM HOLE WITH IN-WALL ACCUMULATOR - A gas turbine engine component is described. The component includes a component wall having an internal surface that is adjacent a flow of coolant and an external surface that is adjacent a flow of gas. The component wall includes a cooling hole that has an inlet defined by the internal surface and an outlet defined by the external surface. The cooling holes also has a metering location having the smallest cross-section area of the cooling hole, an internal diffuser positioned between the inlet and the metering location, an accumulation diverter portion of the internal diffuser and an accumulator portion of the internal diffuser. | 03-17-2016 |
20160076395 | METHOD OF MANUFACTURING ICE PANEL SEGMENTS - The present disclosure relates to methods of manufacturing ice panel segments for turbofan engines. An ice panel material may be wrapped around a mandrel. The ice panel material may include an inner fiberglass layer, a plurality of KEVLAR® layers, and an outer fiberglass layer. The ice panel material may be bagged and cured into a rigid molded cylinder. The rigid molded cylinder may be radially cut into ice panel cylinders. The ice panel cylinders may be axially cut into ice panel segments. The ice panel segments may be bonded to an inner surface of a fan case. | 03-17-2016 |
20160076388 | FAN PLATFORM - A fan platform section may include a flow path portion with a plurality of composite plies. A first composite ply in the plurality of composite plies may include directional fibers. The directional fibers may be configured to prevent twisting of the flow path section in response to a centripetal load. The fan platform section may include a second composite ply in the plurality of composite plies. The second composite ply may include directional fibers. The directional fibers in the first composite ply may be orthogonal with respect to the directional fibers in the second composite ply. | 03-17-2016 |
20160076380 | INCIDENCE-TOLERANT, HIGH-TURNING FAN EXIT STATOR - A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge, an outer diameter edge, a trailing edge and a leading edge. The leading edge has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge. The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction. | 03-17-2016 |
20160076136 | Coated Articles and Manufacture Methods - An article ( | 03-17-2016 |
20160075438 | SYSTEMS FOR GENERATING AUXILIARY ELECTRICAL POWER FOR JET AIRCRAFT PROPULSION SYSTEMS - An aircraft jet propulsion system is disclosed. The aircraft jet propulsion system may comprise a thermoelectric generator array (“TEG” array) coupled to a portion of the aircraft jet propulsion system, wherein the TEG array converts heat energy to electrical energy, and supplies power to the aircraft jet propulsion system, wherein the electrical energy is supplied to a power supply. The aircraft jet propulsion system may comprise an alternator that generates less energy than is required to power the aircraft jet propulsion system. The TEG array may supplement the energy generated by the alternator. The energy generated by the TEG array and the energy generated by the alternator may be sufficient to power the aircraft jet propulsion system and/or the electrical energy generated by the TEG array may be sufficient to power to aircraft jet propulsion system. | 03-17-2016 |
20160069210 | WINDBACK HEAT SHIELD - A heat shield includes a first end configured to connect to an inner engine case at an inner connecting point, and a second end configured to connect to an outer engine case at an outer connecting point. The heat shield also includes a bulge extending in an aft direction from a radially upstream portion. A compressor section and a gas turbine engine including the heat shield are also disclosed. | 03-10-2016 |
20160069204 | GEARED ANNULAR AIRFLOW ACTUATION SYSTEM FOR VARIABLE CYCLE GAS TURBINE ENGINES - An annular airflow control system for a gas turbine engine includes a sync ring rotatable to move the multiple of contra-rotatable variable vanes through a respective multiple of geared interfaces to throttle an airflow through the multiple of contra-rotatable variable vanes. | 03-10-2016 |
20160069200 | Turbine Vane With Platform Pad - A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed. | 03-10-2016 |
20160069198 | CASTING OPTIMIZED TO IMPROVE SUCTION SIDE COOLING SHAPED HOLE PERFORMANCE - A gas turbine engine component includes a pressure side, a suction side, a leading edge, a trailing edge, an outer surface and an inner surface. The inner surface is positioned within the outer surface and defines a core. The inner surface has a first protrusion. | 03-10-2016 |
20160069190 | BEVELED COVERPLATE - A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face. The gas turbine engine also includes a coverplate that includes a first bend, a flat portion substantially parallel to the first mate face and a first wing substantially parallel to the second mate face. | 03-10-2016 |
20160068446 | SYSTEMS AND METHODS FOR CERAMIC MATRIX COMPOSITES - Methods for fabricating a ceramic matrix composite are disclosed. A fiber preform may be placed in a mold. An aqueous solution may be added to the fiber preform. The aqueous solution may include water, carbon nanotubes, and a binder. The preform may be frozen. Freezing the preform may cause the water to expand and separate fibers in the fiber preform. The carbon nanotubes may bond to the fibers. The preform may be freeze dried to remove the water. The preform may then be processed according to standard CMC process. | 03-10-2016 |
20160067820 | SELECTIVE LASER MELTING SYSTEM - An additive manufacturing apparatus comprises a laser beam generator, a build surface spaced apart from the laser beam generator, and first and second adjacent optical elements disposed along a beam travel path between the laser beam generator and the build surface. The first optical element is continuously rotatable about a beam steering axis and the second optical element is continuously rotatable about the beam steering axis independently of the first optical element. | 03-10-2016 |
20160067779 | LOCAL CONTAMINATION DETECTION IN ADDITIVE MANUFACTURING - An additive manufacturing system comprises a build chamber, a powder bed additive manufacturing device disposed in the build chamber, and a powder contamination detection system. The powder contamination detection system is in communication with an atmosphere in the build chamber. | 03-10-2016 |
20160061057 | LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE - According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and 0.45. | 03-03-2016 |
20160060748 | Deposition Apparatus and Methods - A deposition apparatus ( | 03-03-2016 |
20160053627 | FLEXIBLE FEATHER SEAL FOR BLADE OUTER AIR SEAL GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM - An active clearance control system for a gas turbine engine includes an intersegment seal engaged with each pair of a multiple of air seal segments. | 02-25-2016 |
20160053626 | GAS TURBINE ENGINE RAPID RESPONSE CLEARANCE CONTROL SYSTEM WITH AIR SEAL SEGMENT INTERFACE - An active clearance control system of a gas turbine engine includes an air seal segment with a bridge hook having a lugged aperture. | 02-25-2016 |
20160052057 | GAS TURBINE COMPONENT MANUFACTURING - A method of fabricating a gas turbine engine component comprises building and machining a hollow workpiece. The workpiece is built via additive manufacturing to create a coarse structure that turbulates cooling flow. At least a portion of the workpiece is machined via subtractive manufacturing to create a smooth surface that promotes laminar flow. | 02-25-2016 |
20160047281 | EMERGENCY OIL SYSTEM - The present disclosure relates to lubricating oil systems, and more specifically emergency lubricating oil systems. This system continuously circulates oil through and/or from a reserve tank. This system does not utilize compressed air systems during normal operation to deliver lubricating oil. The system described herein does not utilize a piston to transfer lubricating oil from a reserve tank to engine elements. | 02-18-2016 |
20160047273 | Turbofan Engine Main Bearing Arrangement - A turbofan engine ( | 02-18-2016 |
20160047271 | DUCTING PLATFORM COVER PLATE - The present disclosure relates to cooling systems for turbine stators. A stator may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge. | 02-18-2016 |
20160047250 | SHOWERHEAD HOLE SCHEME APPARATUS AND SYSTEM - The gas turbine component showerhead cooling hole layouts described herein include minimal lateral cooling hole exit diffusion on the middle showerhead cooling hole rows and interior facing sides of outer rows. In this way, rows of cooling holes may be placed close together. Stated another way, the outer showerhead cooling hole rows substantially only include lateral cooling hole exit diffusion in the direction away from the other rows to again allow the rows to be placed close together. | 02-18-2016 |
20160040600 | MULTI-AXIAL BRUSH SEAL - A seal assembly, includes a first brush supported between first and second plates, a second brush supported on the first and second plates transverse to the first brush seal, and a third plate attached to the second brush. | 02-11-2016 |
20160040598 | LOW NOISE COMPRESSOR FOR GEARED GAS TURBINE ENGINE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan, a compressor section having a low pressure compressor and a high pressure compressor, a combustor section, and a turbine section having a low pressure turbine, the low pressure turbine for driving the low pressure compressor and the fan; a gear reduction effecting a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor; and at least one stage of the compressor section having a ratio of vanes to blades that is greater than or equal to 1.8. The corrected tip speed of the blades is greater than or equal to 480 ft/sec at an approach speed. | 02-11-2016 |
20160040281 | Spallation-Resistant Thermal Barrier Coating - A coated article has: a metallic substrate ( | 02-11-2016 |
20160033358 | Focused Focused Optical Configuration for NSMS Probes - A method for configuring a sensor of a non-interference stress management system is disclosed. The method may include determining a focal distance between a light transmitting fiber and a transmit lens, the focal distance configured to focus light from the transmit fiber to form a focused transmit beam, the transmit beam targeting a reflective structure. The method may further include positioning the light transmitting fiber and the transmit lens, wherein the light transmitting fiber and the transmit lens are separated by a transmit gap based on the focal distance and positioning a light receptive fiber and a receive lens to receive a focused reflected beam from the reflective structure, wherein the light receptive fiber is separated from the receive lens by a receive gap based on the focal distance. | 02-04-2016 |
20160032937 | GAS TURBINE ENGINE AXIAL DRUM-STYLE COMPRESSOR ROTOR ASSEMBLY - A gas turbine engine includes an axial compressor which includes a rotor assembly including a first rotor segment with a first inner rim, a first sealing surface, and a first aft engagement feature, and a second rotor segment positioned aft of the first rotor segment and having a second inner rim, a second sealing surface, and a second inner rim with a second fore engagement feature that is complementary to the first aft engagement feature. The first and second sealing surfaces are complementary to each other, and are bonded together via a transient liquid phase diffusion process. The first and second sealing surfaces are disposed on the outer rim. The first aft engagement member may be a notch that is complementary to the second fore engagement feature, which may be a shelf. | 02-04-2016 |
20160032838 | Cartridge Style Ejector Pump - In accordance with one aspect of the disclosure, a cartridge style ejector pump for a fluid flow system is disclosed. The ejector pump may have a body defining a flow path therein. The body may be structurally independent of the fluid flow system. The body may further define a suction inlet communicating through the body to the flow path, an outlet communicating through the body from the flow path, and a motive flow inlet communicating through the body to the flow path. | 02-04-2016 |
20160032827 | Turbofan Engine Bearing and Gearbox Arrangement - A turbofan engine ( | 02-04-2016 |
20160032767 | GAS TURBINE ENGINE WITH AXIAL COMPRESSOR WITH INTERNAL COOLING PATHWAYS - A gas turbine engine may include an axial high pressure compressor having an air flow pathway positioned between the inner and outer rim of the rotor section. The air flow pathway includes an inlet port, a transition segment, an axial segment, and an outlet port. The pathway may be a tube having an ovoid cross sectional shape and is substantially co-planar to the outer surface of the outer rim. The pathway may traverse the rotor section from the first rotor segment to the rear hub. | 02-04-2016 |
20160032765 | BEARING COMPARTMENT SEALING SYSTEM WITH PASSIVE COOLING - The present disclosure relates to sealing systems for bearing compartments. In one embodiment, a sealing system includes a runner configured to extend circumferentially around a rotating component, the runner is formed of a material with low radial thermal growth and is configured to tit to the rotating component to remove heat away from the runner. The runner can include an outer surface configured to provide passive cooling for the runner in the bearing compartment. The sealing system can also include a seal configured to operate with the runner, wherein the seal includes a clearance seal on an air side of the runner. The runner can be configured to operate without direct oil cooling. | 02-04-2016 |
20160032757 | Engine Inlet Total Air Temperature Sensor - A total air temperature (TAT) sensor assembly is disclosed. The assembly includes a housing that accommodates a temperature sensor. The assembly also includes a first airfoil that includes a leading end and a trailing end and a second airfoil that includes a leading end and a trailing end. The first and second airfoils are disposed in a spaced-apart fashion that defines a curved passageway so incoming air can flow between the first and second airfoils before engaging the housing and the temperature sensor. The trailing ends of the airfoils are disposed on opposite sides of the housing and spaced apart from the housing to permit air flowing through the curved passageway to pass the housing. | 02-04-2016 |
20160032753 | GAS TURBINE ENGINE WITH AXIAL COMPRESSOR HAVING IMPROVED AIR SEALING - A gas turbine engine including an axial high pressure compressor having expansion slots in the outer rim of the rotor section. The expansion slots may be positioned between blades of a rotor segment. The fore end of the slots may have an axial seal which is coupled to the inner surface of the outer rim in the first rotor segment, and may comprise a fin configuration. The axial seal may be integral to the inner surface of the outer rim. The compressor may comprise a plurality of expansion slots and axial seals, including in a plurality of rotor segments. | 02-04-2016 |
20160032750 | STATIONARY NON-ROTATING BRUSH SEALS - The present disclosure relates to an aircraft brush seal comprising a first brush seal member and a second brush seal member comprising a channel that receives a plurality of interwoven brush fibers. The interwoven brush fibers may be coupled to the first brush seal member and/or may extend into the second brush seal member. The interwoven brush fibers may not couple to the second brush seal member and/or may form an air seal. The air seal may be formed between a first air compartment and a second air compartment. | 02-04-2016 |
20160032735 | TRANSIENT LIQUID PHASE BONDED TIP SHROUD - A composite ceramic turbine blade includes a ceramic airfoil portion and a ceramic outer tip shroud portion. The ceramic outer tip shroud portion is joined to the ceramic airfoil portion by a bonding means. In an embodiment, the bonding means comprises partial transient liquid phase bonding. In another embodiment, the airfoil portion is a fiber reinforced ceramic. | 02-04-2016 |
20160032726 | GAS TURBINE ENGINE AXIAL COMPRESSOR REAR HUB - A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication with the cooling channel. The cooling channels are configured to delivery air to contact the inner surface of the rear hub. | 02-04-2016 |
20160031182 | COMPOSITE FLANGE WITH THREE-DIMENSIONAL WEAVE ARCHITECTURE - According to various embodiments, a carbon fiber structure is presented. The carbon fiber structure may address loads presented to an engine component in various directions. For instance, non-planar surfaces of a composite comprising a structure disclosed herein may achieve enhanced stiffness and/or strength. Thus, delamination of elements comprising a structure disclosed herein may be reduced. A three dimensional weave of carbon fiber elements through-thickness may provide enhanced strength to the composite material. | 02-04-2016 |
20160031006 | Arcuate Directionally Solidified Components and Manufacture Methods - A method for casting comprising: providing a seed, the seed characterized by: an arcuate form and a crystalline orientation progressively varying along an arc of the form; providing molten material; and cooling and solidifying the molten material so that a crystalline structure of the seed propagates into the solidifying material. | 02-04-2016 |
20160025040 | GAS DYNAMIC VALVE - A flow-management system may comprise a center body impermeable to air. A conical surface of the center body may face forward. A blocking surface of the center body may be coaxial with the conical surface and may comprise an annular recess. An annular ring may be aft of the center body and fluidly coupled with the blocking surface. A tube may encase the center body and annular ring. The annular ring may comprise an air-foil shape to direct a pulse to the blocking surface. The blocking surface may comprise a central peak and a circular ridge separated by the annular recess. | 01-28-2016 |
20160025014 | HIGH TEMPERATURE DISK CONDITIONING SYSTEM - A gas-circulation system for conditioning a disk of an aircraft may comprise a first takeoff port configured to extract a combusted gas and a second takeoff port configured to extract an uncombusted gas. A first valve may comprise an inlet in fluid communication with the first and second takeoff ports and an outlet of the first valve in fluid communication with the disk. | 01-28-2016 |
20160025005 | BIFURCATED AIR INLET HOUSING FOR A MINIATURE GAS TURBINE ENGINE - A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths, such that the airflow is generally around 360 degrees of a rotational axis of the gas turbine engine. A rotor and a turbine drive a shaft to drive the rotor with the shaft including a bearing mounted at a location downstream of the nose cone upstream end. | 01-28-2016 |
20160025003 | Turbofan Engine Bearing and Gearbox Arrangement - A turbofan engine ( | 01-28-2016 |
20160024947 | Blade Wear Pads and Manufacture Methods - A blade assembly comprises a blade ( | 01-28-2016 |
20160024946 | ROTOR BLADE DOVETAIL WITH ROUND BEARING SURFACES - A blade for use in a gas turbine engine, the blade having an airfoil portion and a dovetail root portion, wherein the dovetail root portion is dimensioned and configured to enable the blade to rotate within a shaped slot formed in a supporting hub of the engine about a center of rotation that extends parallel to a central axis of the hub in response to an impact force on the airfoil portion of the blade. | 01-28-2016 |
20160024942 | Abrasive Tipped Blades and Manufacture Methods - An article ( | 01-28-2016 |
20160024937 | MULTI-LOBED COOLING HOLE - A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first surface, an outlet located at the second surface, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and having a first downstream end adjacent the outlet and spaced from the inlet by a first distance, a second lobe diverging longitudinally from the metering section and having a second downstream end adjacent the outlet and spaced from the inlet by a second distance different from the first, and a transition region positioned between the lobes, the transition region having a third downstream end adjacent the outlet. | 01-28-2016 |
20160024925 | Turbine Disk Fatigue Rejuvenation - A process for rejuvenating a turbine disk having a plurality of slots includes the steps of determining a depth of a damaged layer containing M23C6 carbide dissolution; and removing the damaged layer from the slots in accordance with the determined depth. | 01-28-2016 |
20160024676 | BIMETALLIC ZINCATING PROCESSING FOR ENHANCED ADHESION OF ALUMINUM ON ALUMINUM ALLOYS - A coated metal component includes an aluminum alloy substrate and a protective aluminum coating on a substrate. An interfacial boundary layer between the coating and substrate enhances coating adhesion. The boundary layer includes isolated regions of copper or tin produced by a double zincating process. The protective aluminum coating exhibits improved adhesion and is formed by electrodeposition in an ionic liquid. | 01-28-2016 |
20160024444 | GEL SOLVENT AND METHOD OF REMOVING DIFFUSION AND OVERLAY COATINGS IN GAS TURBINE ENGINES - A method of stripping an engine component may comprise applying an acidic gel solvent to a coating of a surface of the engine component, leaving the acidic gel solvent on the surface of the engine component for a predetermined duration, and removing the acidic gel solvent from the surface of the engine component. The method may further include mixing an acid with a gelling agent to form the acidic gel solvent. The acid may comprise hydrochloric acid. The gelling agent may comprise a cellulosic material. The gelling agent may comprise a carbohydrate. The method may further include rinsing the acidic gel solvent from the surface of the engine component. The coating may comprise at least one of a diffusion coating or an overlay coating. | 01-28-2016 |
20160017844 | REVERSE CORE ENGINE WITH THRUST REVERSER - An engine system has a gas generator, a bi-fi wall surrounding at least a portion of the gas generator, a casing surrounding a fan, and the casing having first and second thrust reverser doors which in a deployed position abut each other and the bi-fi wall. | 01-21-2016 |
20160017752 | Turbofan Engine Assembly Methods - A method for assembling a turbofan engine ( | 01-21-2016 |
20160017729 | STRUCTURAL GUIDE VANE SONIC SHAPE AND INSPECTION - A method of forming a guide vane is disclosed. The method includes forming a vane blank with sufficient material to fabricate the guide vane in accordance with any one of a plurality of different vane classes. The vane blank is inspected for material inconsistencies, and material is removed from the vane blank to form a desired guide vane in accordance with one of the plurality of vane classes. The inspection process includes disregarding at least one material inconsistency in a region of the vane blank that is re- moved to form the guide vane. | 01-21-2016 |
20160017726 | Coated Articles and Manufacture Methods - An article ( | 01-21-2016 |
20160017725 | Blades and Manufacture Methods | 01-21-2016 |
20160017724 | VARIABLE THICKNESS TRAILING EDGE CAVITY AND METHOD OF MAKING - A method for forming an airfoil includes forming a ceramic core, forming a refractory metal core using additive manufacturing, joining the ceramic core and the refractory metal core to form a hybrid core, and casting the airfoil around the hybrid core. The ceramic core is used to define an internal cavity of the airfoil. The refractory metal core has an upstream end and a downstream end. The upstream end has a lateral thickness greater than a lateral thickness of the downstream end. The refractory metal core is used to define a trailing edge cavity within the airfoil. The trailing edge cavity is in flow communication with the internal cavity of the airfoil and trailing edge slots located on an outer surface of the airfoil near a trailing edge. This method provides for an airfoil having a trailing edge cavity of variably thickness and casting cores used for their manufacture. | 01-21-2016 |
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 |
20160017713 | Turbine Engine Hybrid Rotor - A turbine engine rotor component has a Ti-based first member ( | 01-21-2016 |
20160017712 | Turbine Engine Repair Methods - A method for patching a damaged polymeric erosion coating ( | 01-21-2016 |
20160017501 | Corrosion Protection Material and Method for Protecting Aluminum Coatings - A method for protecting porous aluminum coatings includes the steps of: providing an orsomil suspension; and rating the porous aluminum coating with said orsomil suspension. The porous aluminum coating may be thermally sprayed coating. | 01-21-2016 |
20160017474 | Thermo-Mechanical Fatigue Resistant Aluminum Abradable Coating - An aluminum coating to be deposited on a substrate having a first coefficient of thermal expansion has an aluminum matrix, and particles of a material having a low coefficient of thermal expansion incorporated into the matrix. The particles bond sufficiently well to the aluminum matrix to carry a portion of the mechanical load. | 01-21-2016 |
20160016253 | MULTIPLE WIRE ELECTRON BEAM MELTING - An additive manufacturing system includes an electron beam gun with a multiple of independent wire feeders and a beam control system operable to control the electron beam gun and the multiple of independent wire feeders to maintain a multiple of melt pools to fabricate a three-dimensional workpiece. | 01-21-2016 |
20160006226 | INSTRUMENTATION TRANSFER STRUT - A monolithic lead separator includes a primary lead tube defining a primary channel, a plurality of secondary lead tubes formed monolithically with the primary lead tube, and an instrumentation lead splitter. A cap is positioned in an aperture in the instrumentation lead splitter in a fluid-tight manner. Each of the secondary channels intersects the primary channel. The instrumentation lead splitter is situated at the intersection of the primary channel and the secondary channels. | 01-07-2016 |
20160003165 | COMPACT AERO-THERMO MODEL BASED CONTROL SYSTEM - Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode, wherein the open loop model generates a current state model as a function of the dynamic states and the model input, wherein a constraint on the current state model is based a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the control system and including a series of utilities, the utilities are based on mathematical abstractions of physical properties associated with the component. The model processor may further include an estimate state module for determining an estimated state of the model based on a prior state model output and the current state model of the open loop model. | 01-07-2016 |
20160003156 | HOLLOW-WALL HEAT SHIELD FOR FUEL INJECTOR COMPONENT - A fuel injector component ( | 01-07-2016 |
20160003143 | TURBOMACHINE FAN CLUTCH - A gas turbine engine assembly includes, among other things, a clutch configured to move from a first position to a second position in response to rotation of a gas turbine engine fan at a speed greater than a threshold speed. Whether the clutch is in the first position or the second position, the clutch permits rotation of the gas turbine engine fan in a first direction. When the clutch is in the first position, the clutch limits rotation of the gas turbine engine fan only in an opposite, second direction. The clutch is disposed within a compartment that is accessible and removable via removal of an aft engine cover structure. The clutch is removable on-wing. | 01-07-2016 |
20160003100 | ROLLING ELEMENT BEARING CONFIGURED WITH A GUTTER AND ONE OR MORE FLUID PASSAGES - A rolling element bearing includes a plurality of rolling elements that are arranged circumferentially around an axis, and radially between a bearing inner ring and a bearing outer ring. The inner ring extends axially between a first end and a second end, and includes a plurality of passages that are fluidly coupled with a channel. The passages are arranged circumferentially around the axis. The channel extends axially into the inner ring from the second end, and includes a gutter that extends radially into and axially within the inner ring. | 01-07-2016 |
20160003098 | Compartment Shielding - A gas turbine engine having an engine axis and method of manufacturing the same is disclosed. The gas turbine engine may comprise a fan configured to drive air, a low pressure compressor section having a core flow path and configured to draw in and compress air flowing along the core flow path, a spool configured to drive the fan, and geared architecture configured to adjust the fan speed. The gas turbine engine may also include a housing defining a compartment that encloses the geared architecture. The housing is disposed between the core flow path and the axis, and includes a shielded mid-section that is in thermal communication with the core flow path of the low pressure compressor section. The shielded mid-section includes an outer layer and an insulator adjacent to the outer layer. | 01-07-2016 |
20160003093 | Fan Axial Containment System - A gas turbine engine ( | 01-07-2016 |
20160003087 | EDGE TREATMENT FOR GAS TURBINE ENGINE COMPONENT - A gas turbine engine component according to an exemplary aspect of the present disclosure includes, among other things, a body having a first outer face meeting a second outer face at an intersection, the body having a plurality of apertures extending from an opening in the first outer face to an opening on the second outer face; and a coating filling at least a portion of the plurality of apertures. | 01-07-2016 |
20160003080 | GAS TURBINE ENGINE SEAL ASSEMBLY - A seal assembly is positioned within a cavity that extends circumferentially about an axial centerline of a gas turbine engine. The cavity includes a cavity wall. The seal assembly includes a seal and a seal protector. The seal extends circumferentially within the cavity. The seal protector extends circumferentially within the cavity. The seal protector is positioned between the seal and the cavity wall. The seal protector includes a locating feature that is operative to contact the seal to aid in axially positioning the seal protector relative to the seal. | 01-07-2016 |
20160003077 | GAS TURBINE ENGINE TURBINE VANE RAIL SEAL - A stator vane seal assembly for a gas turbine engine that includes a vane that has a rail with a scallop that extends axially through the rail. A scallop seal obstructs the scallop. | 01-07-2016 |
20160003068 | METHOD FOR DETECTING A COMPROMISED COMPONENT - A method for providing visually detectable changes to a surface that has been subjected to a temperature in excess of a predetermined temperature. A coating is applied to the surface, wherein the coating will melt when the predetermined temperature has been reached. Centrifugal forces acting on the melted coating will cause it to be displaced such that the disturbed surface is visibly detectable upon inspection after solidifying. | 01-07-2016 |
20160003066 | Abrasive Preforms and Manufacture and Use Methods - A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; and an abrasive embedded in the self-braze material; and securing the combination to the substrate. | 01-07-2016 |
20160003065 | Abrasive Coating and Manufacture and Use Methods - A method for applying an abrasive comprises: applying, to a substrate, the integral combination of a self-braze material, an abrasive, a matrix in which the abrasive is at least partially embedded, and an intermediate layer between the self-braze material and the matrix; and heating to cause the self-braze material to braze to the substrate. | 01-07-2016 |
20160003064 | Abrasive Coating and Manufacture and Use Methods - A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; an abrasive; and a matrix in which the abrasive is at least partially embedded; and heating to cause the self-braze material to braze to the substrate. The heating leaves at least a portion of the self-braze material with a composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 0.0-4.5; tungsten 0.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel. | 01-07-2016 |
20160003062 | Fan Blades with Protective Sheaths and Galvanic Shields - Light weight fan blades for turbofan jet engines are disclosed. The fan blades may be fabricated from an aluminum alloy. To enhance the hardness of the leading edge of the fan blade, a titanium sheath may be attached to the leading edges of the fan blades. To prevent galvanic coupling between the titanium and the aluminum, a polymeric liner may be disposed between the protective titanium sheath and the aluminum fan blade. The liner may be fabricated from a polymer material, such as a polyimide or another high performance polymer. | 01-07-2016 |
20160003050 | VARIABLE SPAN SPLITTER BLADE - The presently disclosed embodiments utilize flow from a higher-energy portion of flow within the impeller flow path and inject it into the lower-energy portion of the flow path to re-energize the flow, delaying the onset of, or minimizing, large (and inefficient, entropy-generating) re-circulation zones in the flow field. By making a spanwise cut along the chord length of the splitter blade (variable blade clearance from leading edge to trailing edge), additional secondary flow occurs within the flow passages as the higher pressure flow on the pressure side of the blade can now spill over into the low-pressure suction side of the blade. | 01-07-2016 |
20160003048 | Airfoil with Thickened Root and Fan and Engine Incorporating Same - In accordance with one aspect of the disclosure, an airfoil is disclosed. The airfoil may include a platform and a blade extending from the platform. The blade may have a root proximate the platform and a tip radially outward from the platform. The root may have a greater thickness than a cross-section at about a quarter-span of the blade or greater. | 01-07-2016 |
20160001890 | APU EXHAUST SYSTEM - An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout. | 01-07-2016 |
20160001407 | Leading Edge Sheath Manufacturing Method - A method for manufacturing a protective sheath for a fan blade leading edge is described. The method may comprise generating a preform plate from a stock plate wherein the preform plate has a flattened surface and an inclined surface having a spike flanked by a first side and a second side. The method may further comprise bending the first side and the second side away from the spike to generate a sheath intermediate followed by generating the protective sheath from the sheath intermediate by shaping an outer surface and an inner surface of the sheath intermediate to match the contour of the fan blade leading edge. | 01-07-2016 |
20160001404 | METHODS AND TOOLS FOR USE IN REPAIRING GAS ENGINE TURBINE BLADES - A repair tool and repair method for restoring gas turbine engine blade tips to a predetermined configuration is provided. The repair tool is an electrode that includes a tool body and a number of pins. The repair tool can be used to repair turbine blade tips through an electrical discharge machining process, such as a ram- or sink-type electrical discharge machining process. | 01-07-2016 |
20160001395 | Sequencing of Multi-Pass Laser Shock Peening Applications - A method for laser shock peening (LSP) a workpiece is disclosed. The method may include identifying a geometry of the workpiece, determining a number of applications of LSP upon a first side and a second side of the workpiece, and sequencing the applications among the first side and the second side to minimize distortion. | 01-07-2016 |
20150377142 | LOW SPOOL STARTER SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine comprises a first compressor, a second compressor, a starter generator and a clutch. The starter generator is coupled to the first compressor. The clutch selectively couples the second compressor and the first compressor. The clutch is disposed between a first shaft and a second shaft to engage the first shaft with the second shaft at rest. A flyweight system is engaged with the clutch mechanism to permit freewheeling of the first shaft relative to the second shaft when subject to rotational motion beyond a threshold speed. A method for starting a gas turbine engine comprises engaging a low pressure compressor with a high pressure compressor utilizing a clutch, rotating the low pressure compressor and the high pressure compressor utilizing a starter generator coupled to the low pressure compressor, igniting the gas turbine engine, and disengaging the clutch at an operational speed of the gas turbine engine. | 12-31-2015 |
20150377137 | ADJUSTABLE CABLE FOR EXHAUST DUCT LINER HANGER - A hanger includes a connector assembly for coupling the hanger to a first annular duct, a bracket for coupling the hanger to a second annular duct concentrically disposed within the first annular duct, and a cable formed by a plurality of wires bound together that extend from the connector assembly to the bracket. A plurality of circumferentially-spaced hangers placed in tension support an exhaust duct liner relative to an exhaust duct. The hangers permit circumferential and axial displacement at each hanger of the exhaust duct liner relative to the exhaust duct. The displacement of the exhaust duct liner relative to the exhaust duct at each hanger is permitted in a first radial direction that decreases tension in the cable and is restrained in a second radial direction that increases tension in the cable. | 12-31-2015 |
20150377129 | De-Icing by Integral Electric Heat Generation - Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil operatively associated with a first rotating surface of the fan; a magnet operatively associated with a second rotating surface of the fan, the second rotating surface rotating in a direction counter to the first rotating surface, the magnet and the electrical coil thereby producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil. | 12-31-2015 |
20150377072 | REPAIR OF SURFACE DAMAGE AT EDGES OF CELLULAR PANELS - A method of working a non-conforming exhaust sleeve utilizes a first plate disposed over an outer surface of an exhaust sleeve and a second plate disposed over an inner surface. The exhaust sleeve includes an aft sleeve attached to an aft edge of a cellular layer and the first plate extends from the cellular layer onto the aft sleeve. The second plate is disposed along the inner surface of the cellular layer. A first plurality of fasteners secures the first plate to the second plate through the cellular layer and a second plurality of fasteners secures the first plate to the aft sleeve. | 12-31-2015 |
20150377051 | SLIDING SEAL - The present disclosure relates generally to a sliding seal between two components. At least one of the two components includes a ramped surface on which the sliding seal slides during relative movement between the two components. | 12-31-2015 |
20150375867 | Engine Mount Waiting Fail Safe Lug Joint with Reduced Dynamic Amplification Factor - An engine mount may include a clevis and a lug defining a hole therethrough. A pin may be joined to the clevis and may extend through the hole of the lug with the pin and the lug defining a clearance therebetween. A trigger system may be disposed on the lug and operatively associated with the pin. | 12-31-2015 |
20150375297 | GAS TURBINE ENGINE COMPONENT COOLING PASSAGE AND SPACE EATING CORE - A method of manufacturing a component that includes providing a core structure, casting a component about the core structure, removing a first portion of the core structure from the cast component, and leaving a second portion of the core structure in the cast component to provide a reduced cross-section in the cast component. | 12-31-2015 |
20150369490 | GAS TURBINE ENGINE COMBUSTOR LINER ASSEMBLY WITH CONVERGENT HYPERBOLIC PROFILE - A heat shield for a combustor of a gas turbine engine includes a first edge with a first set of cantilevered members and a second edge with a second set of cantilevered members. | 12-24-2015 |
20150369173 | Exhaust Liner Flange Cooling - A liner portion has an exhaust liner portion with an inner face extending to an outward extending flange. Cooling grooves formed in the flange have a radially outward inlet point and a radially inner outlet point. A flow area at the inlet point is smaller than the flow area at the outlet point. | 12-24-2015 |
20150369131 | AXIAL TENSION SYSTEM FOR A GAS TURBINE ENGINE CASE - A gas turbine engine includes a convex case section. The convex case section includes an upstream case portion having a first radius, a downstream case portion having a second radius, and an intermediate case portion between the upstream case portion and the downstream case portion. The intermediate case portion has a third radius larger than the first radius and the second radius. A tension rod extends from the upstream case portion to the downstream case portion. | 12-24-2015 |
20150369130 | SYSTEMS AND METHODS FOR DISTRIBUTING COOLING AIR IN GAS TURBINE ENGINES - Systems and methods are disclosed herein for distributing cooling air in gas turbine engines. A tangential on board injector (“TOBI”) may supply cooling air to a turbine section of a gas turbine engine. The cooling air may be split into a first cooling air path and a second cooling air path. The first cooling air path may fluidly connect the TOBI and the interior of a first stage rotor blade. The second cooling air path may fluidly connect the TOBI and a cavity. The cavity may be located between a first disk and a second disk. The cooling air paths from a single cooling air source may thermally isolate portions of the turbine section. | 12-24-2015 |
20150369083 | LATCHING ACTUATION MECHANISM FOR NACELLE MOUNTED LATCHING SYSTEM - An assembly for a gas turbine engine includes a first fan cowl pivotable on a hinge from a first position to a second position. A latching actuation mechanism is disposed under the nacelle, engages the hinge, and is actuated by movement of the hinge between the first position and the second position. | 12-24-2015 |
20150369067 | STRUCTURAL GUIDE VANE OUTER DIAMETER K GUSSETS - A guide vane includes an airfoil with a first end and a second end. A platform is disposed at a first end of the airfoil, and a K-gusset is disposed on the platform opposite the airfoil. The K-gusset includes four bosses and ribs extending between the bosses in a “K” configuration. | 12-24-2015 |
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 |
20150362192 | GAS TURBINE ENGINE COMBUSTOR LINER ASSEMBLY WITH CONVERGENT HYPERBOLIC PROFILE - A liner assembly for a combustor of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a support shell with a convex profile which faces the heat shield. A further embodiment of the foregoing embodiment of the present disclosure is where the convex profile is defined by a hyperbolic cosine function. A further embodiment of any of the foregoing embodiments of the present disclosure is where the convex profile provides an approximate 4.5 inlet-to-exit area ratio. A further embodiment of any of the foregoing embodiments, of the present disclosure wherein the convex profile provides a flow acceleration toward approximately 0.5 Mach towards an end of a convergent section. | 12-17-2015 |
20150361898 | Heat Shield for Gas Turbine Engine Gearbox - A heat shield ( | 12-17-2015 |
20150361887 | GAS TURBINE ENGINE WITH GEARED TURBOFAN AND OIL THERMAL MANAGEMENT SYSTEM WITH UNIQUE HEAT EXCHANGER STRUCTURE - An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler. | 12-17-2015 |
20150361829 | FLUID COLLECTION GUTTER FOR A GEARED TURBINE ENGINE - A turbine engine system includes a gutter and a gear train with an axial centerline. The gutter is disposed radially outside of the axial centerline. The gutter at least partially circumscribes the gear train, and includes an inner surface and a channel. The channel receives fluid directed out of the gear train. The channel extends radially into the gutter from the inner surface to a channel end, and circumferentially to a channel outlet. At least a portion of the channel has a cross-sectional channel geometry that tapers axially as the channel extends radially towards the channel end. | 12-17-2015 |
20150361827 | Acoustic Treatment to Mitigate Fan Noise - A cooling manifold has a plurality of pieces. The pieces extend in a circumferential direction to abutting flanges. The flanges are secured together at circumferential ends of each piece. Cooling channels are formed in between inner and outer walls. Air inlets are formed in the pieces with the air inlets delivering air in the interior. There are fingers on an outer periphery. The fingers are aligned within an air outlet. The air can be delivered into the inlet, cool the interior, and leave through the outlet extending to a main conduit. The main conduit is secured directly to an outer periphery of the cooling manifold. | 12-17-2015 |
20150361824 | Gas Turbine Engine with Low Fan Noise - In accordance with one aspect of the disclosure, a gas turbine engine, method of using and designing such is disclosed. The gas turbine engine may comprise a fan including a plurality of blades, and a variable area fan nozzle. The fan may be configured to have a design point fan tip leading edge relative flow angle β | 12-17-2015 |
20150361811 | MULTI-CIRCUIT LUBRICATION SYSTEM FOR A TURBINE ENGINE - A turbine engine system includes a first lubricant circuit, a second lubricant circuit, a plurality of engine stages and a shaft. The first lubricant circuit includes a first turbine engine component that is fluidly coupled with a first lubricant heat exchanger. The first turbine engine component includes a gear train, which connects a first of the engine stages to a second of the engine stages. The second lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger. The second lubricant circuit is fluidly coupled with the first lubricant circuit, and the second turbine engine component includes a bearing. The shaft is supported by the bearing, and connected to one of the engine stages. | 12-17-2015 |
20150361801 | FLUID DAMPER AND METHOD OF MAKING - An airfoil includes an airfoil structure defining a damping network that includes a first cavity, a second cavity, a flow passage connecting the first and second cavities. The airfoil further includes a damping material configured to flow through the damping network. A method of forming an airfoil includes forming an airfoil body having a damping network that includes a first cavity, a second cavity, and a flow passage connecting the first and second cavities. The method further includes adding a damping material configured to flow through the damping network. | 12-17-2015 |
20150361556 | Deposition Apparatus and Use Methods - A deposition apparatus comprises: an infeed chamber; a preheat chamber; a deposition chamber; and optionally at least one of a cooldown chamber and an outlet chamber. At least a first of the preheat chamber and the cooldown chamber contains a buffer system for buffering workpieces respectively passing to or from the deposition chamber. | 12-17-2015 |
20150361543 | Suspension Plasma Spray Apparatus and Use Methods - A suspension plasma spray feeder apparatus for delivering a suspension from a suspension source to a plasma spray gun. The feeder apparatus comprises a suspension line and a vibrator mounted to vibrate the suspension line. | 12-17-2015 |
20150360289 | HYBRID ADDITIVE MANUFACTURING METHOD - An additive manufacturing method for forming a component is disclosed. The method includes the steps of forming a first layer of additive material on a substrate. The first layer of additive material is deep rolled. A second layer of additive material is then formed on the first layer of additive material. | 12-17-2015 |
20150355145 | PHASED ARRAY BILLET DATA EVALUATION SOFTWARE - A computer-implemented method for evaluating echo signals obtained from a phased array experiment on a billet is disclosed. The computer-implemented method may comprise collecting the echo signals from a pulser/receiver unit, correlating the echo signals with a position on a longitudinal axis and a circumferential angle of the billet, computing an amplitude for each of the echo signals, displaying the amplitudes as indications in a c-scan data plot at a computer display unit, and determining the signal-to-noise ratios of indications located in a region-of-interest box relative to noise in surrounding boxes in the c-scan data plot. The computer-implemented method may further comprise classifying each indication as rejectable, reportable, or insignificant based on its amplitude and signal-to-noise ratio. The computer-implemented method may find applications in quality control evaluations in the aircraft industry. | 12-10-2015 |
20150354821 | Cumbustor Liners with U-Shaped Cooling Channels - A combustor having U-shaped cooling channels is disclosed. The combustor may include a shell having an impingement hole, a liner spaced from the shell and having an effusion hole; a first partition spanning between the shell and the liner, a second partition spaced from the first partition and spanning between the shell and the liner; and a U-shaped channel defined between the shell and the liner and defined in part by the wall, the channel having upstream and downstream ends both adjacent the first partition and separated by the wall, wherein the impingement hole communicates with the upstream end and the effusion hole communicates with the downstream end. | 12-10-2015 |
20150354819 | Combustor Cooled Quench Zone Array - In accordance with one aspect of the disclosure, a combustor is disclosed. The combustor may include a shell and a liner disposed within the shell. The combustor may further include a grommet at least partially defining a hole communicating through the shell and liner and a cooling channel communicating through the grommet. | 12-10-2015 |
20150354413 | TURBINE EXHAUST CASE MULTI-PIECE FRAME - A turbine exhaust case ( | 12-10-2015 |
20150354409 | PLUG ASSEMBLY WITH RETAINING ELEMENT - The present disclosure relates to plug assemblies within a gas turbine engine. In one embodiment, a plug assembly includes a boss which includes a shaft and a collar, a retaining element including at least two prongs, and a plug including a shank and at least one retaining feature. The at least two prongs of the retaining element are configured to retain the plug to the boss. | 12-10-2015 |
20150354407 | LUBRICATING FLUID DAMPED ANTI-ROTATIONAL SYSTEMS - A lubricating fluid damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation and a radial aperture, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a lubricating fluid jet configured to propel a lubricating fluid through the radial aperture toward the contact portion. | 12-10-2015 |
20150354406 | BLADE OUTER AIR SEAL AND METHOD OF MANUFACTURE - The present disclosure relates to gas turbine engine components, such as blade outer air seals and methods of manufacture. In one embodiment, a gas turbine engine component includes a retention interface formed by an additive manufacturing process. The gas turbine engine component can include a retention interface having a pattern, and a thermal barrier layer formed to the retention interface. | 12-10-2015 |
20150354405 | COMPOSITE ARTICLE HAVING METAL-CONTAINING LAYER WITH PHASE-SPECIFIC SEED PARTICLES AND METHOD THEREFOR - A composite article includes a substrate and a metal-containing layer on the substrate. The metal of the metal-containing layer is oxidizable to a plurality of different oxide phases. The metal-containing layer includes a plurality of phase-specific seed particles promoting formation of a selected one of the different oxide phases. | 12-10-2015 |
20150354385 | FLAPPER SEAL APPARATUS AND SYSTEM - An engine component for isolating a first pressure and/or first flow and a second pressure and/or second flow is provided. The engine component may comprise a body portion, a first seal element and a second seal element. The body portion may include a first standoff and a second standoff. The first seal element housed within the body portion. The second seal element may also be housed within the body portion. The second seal element may be coupled to the first seal element. | 12-10-2015 |
20150354384 | BUMPER FOR SEALS IN A TURBINE EXHAUST CASE - A turbine seal system comprises a structural frame, a structural member, a seal and a bumper. The structural member is disposed opposite the structural frame. The seal extends between the structural frame and the structural member. The bumper is anchored to the structural frame or the structural member and extends toward a mid-region of the seal. In one embodiment, the structural frame comprises a ring-strut-ring turbine exhaust case. | 12-10-2015 |
20150354372 | GAS TURBINE ENGINE COMPONENT WITH ANGLED APERTURE IMPINGEMENT - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion that includes a first wall spaced apart from a second wall. At least one rib extends between the first wall and the second wall and at least one aperture extends through the at least one rib. The at least one aperture is angled relative to a radial axis of the at least one rib. | 12-10-2015 |
20150354358 | Post-Peen Grinding of Disk Alloys - A process for forming a metallic article comprises: peening a precursor to create a residual stress distribution and a region of slip bands; and surface machining the precursor to substantially remove the slip band region while leaving a substantial amount of the residual stress distribution. | 12-10-2015 |
20150354081 | Abrasive Tip Blade Manufacture Methods - A method is provided for manufacturing a blade. The blade comprises an airfoil ( | 12-10-2015 |
20150345400 | FRAME JUNCTION COOLING HOLES - A module for a gas turbine engine comprises a frame and a frame cooling system. The frame includes a circumferentially distributed plurality of radially extending struts. Each strut is joined to an outer frame section at an outer frame junction, and joined to an inner frame section at an inner frame junction. The frame cooling system comprises an inlet, a plurality of cooling air passages extending from the inlet radially through each of the plurality of frame struts; and an outlet. The outlet is in fluid communication with at least one of the cooling air passages and includes a film cooling hole formed through the frame proximate the outer frame junction. | 12-03-2015 |
20150345338 | TURBINE FRAME ASSEMBLY AND METHOD OF DESIGNING TURBINE FRAME ASSEMBLY - A structural case assembly comprises a frame, fairing and heat shield. The frame is fabricated from a material having a temperature limit below an operating point of a gas turbine engine, and comprises an outer ring, an inner ring and a plurality of struts extending therebetween to define a flow path. The fairing is fabricated from a material having a temperature limit above the operating point of the gas turbine engine, and comprises a ring-strut-ring structure that lines the flow path. The heat shield is disposed between the frame and the fairing to inhibit radiant heat transfer therebetween. The heat shield may block all line-of-sight between the fairing and the frame. The frame may be produced from CA-6NM alloy. A method for designing a turbine case structure includes selecting a frame material having a temperature limit below the operating point of an engine. | 12-03-2015 |
20150345330 | MULTI-PIECE HEAT SHIELD - An assembly for a gas turbine engine includes a first casing, a fairing, and a multi-piece heat shield assembly. The fairing is disposed adjacent the first casing. The multi-piece heat shield assembly includes a first shield mounted to the first casing and extending between the first casing and the fairing, and a second shield mounted to the fairing and extending between the fairing and the first casing. | 12-03-2015 |
20150345329 | HEAT SHIELD FOR A CASING - A gas turbine engine includes a casing, a fairing, and a heat shield. The fairing is annularly shaped and disposed adjacent the casing. The heat shield is connected to the casing and includes a first portion and a second portion. The first portion is generally cylindrically shaped and extends between the fairing and the casing and the second portion extends generally radially away from the casing and the first portion toward the fairing. | 12-03-2015 |
20150345320 | FAN CASE WITH AUXETIC LINER - A case for fan includes a multilayer structure formed of cylindrical layers, including an outer shell and a liner layer. The liner layer is located radially inward from the shell. The liner layer is an auxetic material, which increases strength to increase effectiveness of case in a blade out condition. | 12-03-2015 |
20150345304 | GAS TURBINE ENGINE COMPONENT HAVING VASCULAR ENGINEERED LATTICE STRUCTURE - A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure. | 12-03-2015 |
20150345299 | SYSTEMS AND METHODS FOR PRE-STRESSING BLADES - A system and methods are provided for pre-stressing blade elements for a gas turbine engine. In one embodiment, a method includes rotating a blade element relative to an axis. The method may also include controlling rotational speed of the blade element to generate residual stress in the blade element. The method may also include rotating multiple blade elements and fan blade units to generate residual stress. Blade elements may be rotated to exceed a maximum operating speed of the blade element to 120% of the maximum operating speed of the blade element. | 12-03-2015 |
20150345298 | GAS TURBINE ENGINE COMPONENT HAVING VASCULAR ENGINEERED LATTICE STRUCTURE - A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure. | 12-03-2015 |
20150337891 | LINKAGE WITH SPHERICAL OR JOURNAL BEARING ASSEMBLY - An assembly includes a spherical bearing race and a spherical bearing element. The bearing race includes a race first segment, a race second segment and a bore that extends along an axis into the bearing race. The bore also extends radially within the bearing race between the first segment and the second segment. The bearing element is arranged within the bore, and radially engages the first segment and the second segment. | 11-26-2015 |
20150337667 | AIRFOIL COOLING DEVICE AND METHOD OF MANUFACTURE - An airfoil has an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure. A swirl structure is operatively associated with the cooling passage and configured to impart a tangential velocity to the cooling medium flowing through the cooling passage. An airfoil has an airfoil structure that defines a first cooling passage and a second cooling passage for directing cooling medium through the airfoil structure, each cooling passage having a swirl structure that imparts tangential velocity on the cooling medium flowing through the associated cooling passage. A method of making an airfoil that includes forming an airfoil structure that defines a cooling passage for directing a cooling medium through the airfoil structure and forming a swirl structure that is operatively associated with the cooling passage and imparts tangential velocity to the cooling medium flowing through the cooling passage. | 11-26-2015 |
20150336037 | Fuel System with Ice and Large Debris Separator Filter - A filter includes an outlet from a container, the outlet transverse to said inlet. A filter screen within the container that segregates the outlet. | 11-26-2015 |
20150330300 | TWO SPOOL ENGINE CORE WITH A STARTER - A gas turbine engine has a first spool, a second spool, and a one-way clutch connecting the first and second spools. The one-way clutch disengages from the second spool when the first and second spools rotate at a predetermined speed. | 11-19-2015 |
20150330248 | HEAT SHIELD FOR COOLING A STRUT - An assembly for a gas turbine engine includes a strut and a heat shield. The heat shield is disposed adjacent the strut and the heat shield and is adapted to contain a cooling air flow that passes along first cavity between the heat shield and the strut. | 11-19-2015 |
20150330230 | TIP LEAKAGE FLOW DIRECTIONALITY CONTROL - An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control vane is formed with an outer surface of the tip wall and a winglet is formed at a junction between the suction sidewall and the tip leakage control vane. | 11-19-2015 |
20150330229 | TIP LEAKAGE FLOW DIRECTIONALITY CONTROL - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall, a tip leakage control channel recessed into an outer surface of the tip wall, a tip leakage control vane integrally formed on the tip wall adjacent to the tip leakage control channel and an air seal radially outward of the tip wall and positioned to minimize leakage at the tip wall. | 11-19-2015 |
20150330227 | BLADES AND BLADE DAMPERS FOR GAS TURBINE ENGINES - A blade damper for a gas turbine blade includes a blade damper body with a first damping surface and a second damping surface. The first damping surface is on a first side of the damper body and the second damping surface is on a second side of the damper body opposite the first damping surface for providing full functionality in both flipped and unflipped orientations. | 11-19-2015 |
20150328681 | Multi-Shot Casting - An alloy part is cast in a mold ( | 11-19-2015 |
20150322809 | Blade Rub Material - One aspect of the disclosure involves a nib material comprising a polymeric matrix and carbon nanotubes 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 1.0 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 carbon nanotubes at least locally have a concentration of 1-20% by weight. | 11-12-2015 |
20150322805 | BLADE UNDERROOT SPACER WITH HOOK REMOVAL - A rotor for use in a gas turbine engine has rotor slots receiving a blade. The blades have an airfoil extending from a dovetail, and the dovetail is received by a rotor slot. A spacer is positioned between an inner wall of the dovetail and an outer wall of the slot, and the spacer is formed with a removal slot. A spacer, a gas turbine engine, and a method are also disclosed. | 11-12-2015 |
20150322797 | BLADE ELEMENT CROSS-TIES - A blade element and methods of manufacturing blade elements are provided for blade elements of a gas turbine engine. In one embodiment, a blade element includes a first inner surface of the blade element, wherein the first inner surface is associated with a first outer blade surface of the blade element, and a second inner surface of the blade element, wherein the second inner surface is associated with a second outer blade surface of the blade element and wherein the second inner surface is opposite from the first inner surface. The blade element may also include a cross-tie configured to connect the first inner surface to the second inner surface, wherein the cross-tie is positioned along a trailing edge of the blade element and the cross-tie is configured to reduce vibration mode effects of the blade element. | 11-12-2015 |
20150322584 | SYSTEM AND METHODS FOR ELECTROCHEMICAL GRINDING WITH A SCREEN - A system and methods are provided for electrochemical grinding a workpiece. In one embodiment, a method includes controlling potentials to grinding tool and the workpiece, controlling applying electrolyte, and controlling grinding of the workpiece by the grinding tool. The method may also include determining screen replacement when there is sufficient metal plated. | 11-12-2015 |
20150321297 | SYSTEMS AND METHODS FOR REPAIRING A SURFACE OF DAMAGED METAL COMPONENTS - A structural element and method for repairing a damaged portion of the metal component comprising a repair material and a layer of diffusive metal material, the metal component comprising a material having a first melting point and the repair material comprising a material having a second melting point that is lower than the first melting point. The repair material also includes an additive material, which diffuses at least partially into the layer of diffusive metal material. The repair material may comprise a cobalt or nickel-boron composition. The repair material may also have a melting point that is approximately 40 degrees Fahrenheit lower than the melting point of the metal component. | 11-12-2015 |
20150321296 | REPAIR MATERIAL PREFORM - A structural element and method for repairing a damaged portion of a metal component utilizes a preform configured to engage with the metal component and receive a repair material. The preform may be made of a material having a first melting point, and the repair material may be made of a material having a second melting point that is lower than the first melting point. The preform may be a mold configured to reconstruct the shape of the damaged portion of the metal component. The repair material may include a first material and an additive material, such as boron. The repair material may have a melting point that is approximately 40 degrees Fahrenheit lower than the melting point of the metal component. | 11-12-2015 |
20150321249 | Hybrid Turbine Blade for Improved Engine Performance or Architecture - A method is provided for casting an article such as a blade having an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The method comprises introducing a molten alloy into a mold; and varying a composition of the introduced alloy during the introduction so as to produce a compositional variation. | 11-12-2015 |
20150316677 | CAPACITIVE PROBE FABRICATING FROM SPRAY DEPOSITION - A proximity sensor includes a lead supported on an outer surface of a case structure and a sensor wire that extends from the lead and through an opening in the case structure. The sensor is formed by applying alternating layers of electrically conductive and non-conductive materials in a non-cured state. A base non-conductive layer is applied to an inner surface of the case structure around the sensor wire in a non-cured state. Once cured, a conductive layer is deposited onto the base non-conductive layer and encapsulates the sensor wire. A cover non-conductive layer is then deposited over portions of the conductive layer to insulate the conductive layer. Portions of the non-conductive layer are then removed such that an area of the conductive layer is exposed to define a sensor area. | 11-05-2015 |
20150315925 | GAS TURBINE SEAL ASSEMBLY AND SEAL SUPPORT - A gas turbine engine assembly includes a second module interconnected with a first module along a joint such that a surface of a second radial wall faces a surface of a first radial wall, with a cavity defined in part by the first and second radial walls. A seal assembly includes a finger seal, and a seal support ring having a backing ring portion and a flow discourager arm. The backing ring is secured to one of the first radial wall and the second radial wall, and the flow discourager arm extends axially through the cavity into a recess formed in the other of the first and second radial walls. The finger seal includes a free end contacting an inner side of the flow discourager arm. | 11-05-2015 |
20150315918 | SHROUDED TURBINE BLADE WITH CUT CORNER - A method includes determining a vibration characteristic of a shrouded turbine blade, which includes an airfoil attacked to a shroud. A corner of the shrouded turbine blade can be removed after determining the vibration characteristic. | 11-05-2015 |
20150315916 | PLATFORM WITH CURVED EDGES - A gas turbine engine component includes an airfoil and a platform. The airfoil has a pressure side and an opposite suction side. The platform is connected to the airfoil and has a first curved edge to the suction side of the airfoil and a second curved edge to the pressure side of the airfoil. The first and second curved edges extend along a surface of the platform having a neutral elevation with respect to a reference axisymmetrical platform surface for the gas turbine engine. | 11-05-2015 |
20150308510 | SYSTEMS AND METHODS FOR ENGINE BEARINGS - Systems and methods are disclosed herein for bearings in a gas turbine engine. A bearing system may include a squirrel cage and a bearing support cage coupled to the squirrel cage. The bearing support cage may include an outer race and a fenestrated cone. The bearing support cage may include a support cage anti-rotation tab adjacent to the outer race. The bearing system may include a housing coupled to the squirrel cage. The housing may include a housing anti-rotation tab. The support cage anti-rotation tab and the housing anti-rotation tab may prevent the bearing system from twisting. | 10-29-2015 |
20150308348 | CONTINUOUS DETONATION WAVE TURBINE ENGINE - A gas turbine engine includes a transient plasma igniter in communication with a continuous detonation wave combustor. A method of operating a gas turbine engine includes maintaining ignition of a continuous detonation wave combustor with a transient plasma igniter. | 10-29-2015 |
20150308341 | COMPRESSOR INJECTOR APPARATUS AND SYSTEM - Cooling systems for high pressure compressor systems are provided. The cooling systems may comprise tangential on board injectors (“TOBIs”). The TOBIs may comprise one or more fluid channels configured to conduct cooling fluid flow to components of the compressor, including, for example, disk-hub portions of the compressor. In this regard, the TOBI may be configured to exhaust cooling air in a manner such that the exhausted air has a similar linear velocity of the disk-hub portion. The cooling air may also be exhausted in a manner that is substantially parallel to the disk-hub portion. | 10-29-2015 |
20150300918 | COMBUSTOR FLAMEOUT DETECTION LOGIC - A method for detecting a flame condition in a combustor of an engine is disclosed. The method may include detecting a temperature of an exhaust gas from the engine, and determining the flame condition in the combustor based on the detected temperature. | 10-22-2015 |
20150300401 | MOMENT RELIEF BARREL WASHER - A barrel washer comprising a convex portion, a concave portion, the concave portion configured to mate with the convex portion, such that the convex portion is only capable of rocking along a single axis within the concave portion. The barrel washer may be configured to prevent a bolt from rotating within the barrel washer. The barrel washer may be configured to relieve bending stress on the bolt as well as extraction of the bolt from the barrel washer. A surface of the concave portion may be coated with a lubricant. A surface of the convex portion may be coated in a lubricant. The barrel washer may be configured to couple a bolt to a flange that is couple to another flange. The convex portion may comprise a rocker. The barrel washer may be configured relieve bending stress on the bolt as a first flange moves relative to a second flange. | 10-22-2015 |
20150300264 | GEARED TURBOFAN ARCHITECTURE FOR REGIONAL JET AIRCRAFT - A gas turbine engine comprises an upstream compressor rotor and a downstream compressor rotor, each having a first stage blade row and a tip speed defined at the first stage blade row. A ratio of the tip speed of the first stage of the downstream compressor rotor to the tip speed of the first stage in the upstream compressor rotor is equal to or above about 1.18. | 10-22-2015 |
20150300250 | TWO SPOOL GAS GENERATOR TO CREATE FAMILY OF GAS TURBINE ENGINES - A method of configuring a plurality of gas turbine engines includes the steps of configuring each of the engines with respective ones of a plurality of propulsors. Each propulsor includes a propulsor turbine and one of a fan and a propeller. Each of the engines is configured with respective ones of a plurality of substantially mutually alike gas generators, with the respective propulsor turbine driven by products of combustion downstream of the gas generator. | 10-22-2015 |
20150300205 | SYSTEMS AND METHODS FOR ANTI-ROTATIONAL FEATURES - Systems and methods are disclosed for anti-rotation lugs. A stator for a gas turbine engine may comprise an outer shroud, an inner shroud, and a plurality of vanes located between the outer shroud and the inner shroud. A plurality of anti-rotation lugs may be coupled to the inner shroud. The anti-rotation lugs may be configured to contact a diffuser case in order to prevent rotation of the stator. The anti-rotation lugs may comprise a body and a tapered shoulder. The tapered shoulder may distribute stress concentrations in the anti-rotation lugs. | 10-22-2015 |
20150300195 | BLADE OUTER AIR SEAL WITH CORED PASSAGES - A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook. | 10-22-2015 |
20150298261 | MITIGATING DISTORTION OF COATED PARTS DURING LASER DRILLING - A method for drilling holes in a part includes positioning the part relative to a laser source, applying a first stress to the part, and applying a laser from the laser source to the part to drill a hole therein, wherein the first stress which is present during the application of the laser counteracts a second stress induced by the application of the laser. | 10-22-2015 |
20150292578 | SYSTEMS AND METHODS FOR SHOCK LOAD REDUCTION - A pawl carrier system comprising a pawl hub disposed substantially coaxially to a pawl carrier, a spring circumferentially disposed between the pawl hub and the pawl carrier, a pawl pivotably mounted to the pawl hub on a pivot joint, the pivot joint comprising an axially extending pin mounted to the pawl hub, wherein the axially extending pin extends through the pawl carrier and the pawl hub. A ratchet carrier system is provided comprising a ratchet carrier disposed substantially coaxially to a ratchet hub, wherein the ratchet hub comprises a ratchet tooth, a spring circumferentially disposed between the ratchet carrier and the ratchet hub and a retaining pin axially extending through the ratchet carrier and the ratchet hub; | 10-15-2015 |
20150292577 | DAMPED ANTI-ROTATIONAL SYSTEMS - A damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a stop pin axially disposed in the pawl carrier and configured to contact the contact portion of the pawl in response to radially inward movement of the pawl, wherein the stop pin is mounted to the pawl carrier at a forward portion of the stop pin and an aft portion of the stop pin, wherein a forward O ring is disposed on the forward portion of the stop pin and an aft O ring is disposed on the aft portion of the stop pin. | 10-15-2015 |
20150292575 | ANTI-ROTATIONAL SYSTEMS AND METHODS - An anti-rotational system is provided comprising a pawl carrier mounted for rotation within a ratchet, the pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, wherein the pivot joint is between the contact portion and the counterweight portion, wherein the counterweight portion is configured to be radially inward of the contact portion in response to rotation of the pawl carrier in a first rotational direction at an angular velocity less than a predetermined angular velocity. | 10-15-2015 |
20150292437 | GAS TURBINE ENGINE CONVERGENT/DIVERGENT EXHAUST NOZZLE DIVERGENT SEAL WITH DOVETAIL INTERFACE - A divergent flap seal includes a flap seal body with a spine, the flap seal body manufactured of a non-metallic material. A mount is engaged with the spine at the dovetail interface and a resilient member at the dovetail interface. | 10-15-2015 |
20150292353 | HIGH PRESSURE COMPRESSOR THERMAL SHIELD APPARATUS AND SYSTEM - In various embodiments, a high pressure compressor may comprise a thermal shield. The thermal shield may be installed between a first rotor and a second rotor. The thermal shield may also be installed radially inward of a stator. The stator may be a shrouded stator. Moreover, the thermal shield may be configured to thermally isolate and/or reduce the thermal load associated with windage on a rotor hub. | 10-15-2015 |
20150285837 | APPARATUS AND METHOD FOR FACILITATING TRANSMISSION OF A WIRELESS SIGNAL FROM EMBEDDED SENSORS - An embedded sensor apparatus for enabling wireless signal transmission while protecting an embedded sensor is disclosed. In various embodiments, an embedded sensor apparatus may comprise a substrate with a cavity, a wireless sensor embedded in the cavity of the substrate, a protective cover coupled to the wireless sensor, and a ferrite layer covering the protective cover. Further, the embedded sensor apparatus may comprise an electromagnetic reflector coupled between the wireless sensor and the substrate. In addition, the ferrite layer may be a ferrite plug, a deposited ferrite layer, or a combination thereof. Furthermore, in various embodiments, covering the protective cover with the ferrite layer may comprise depositing the ferrite layer on the protective cover using a cold spray process. In another embodiment, covering the protective cover with the ferrite layer may comprise depositing the ferrite layer on the protective cover using a thermal spray process. | 10-08-2015 |
20150285148 | CARBURETED FUEL INJECTION SYSTEM FOR A GAS TURBINE ENGINE - A fuel injection system for a gas turbine engine includes a vane in an airflow path within the gas turbine engine, the vane includes an air channel with an outlet in communication with the airflow path; and a fuel nozzle within the vane operable to inject fuel into the air channel to at least partial premix and prevaporize the fuel with a secondary airflow from within the vane in the air channel prior to entry into the airflow path through the outlet. A method of injecting fuel within a gas turbine engine includes at least partially premixing and prevaporizing fuel with a secondary airflow from within a vane in an air channel within the vane, the vane within an airflow path of the gas turbine engine. | 10-08-2015 |
20150284067 | STABILIZER WITH STRUCTURAL BOX AND SACRIFICIAL SURFACES - An aircraft includes a tail extending from a fuselage. The tail defines a structural box having first and second vertical stabilizers that support a horizontal stabilizer. The tail includes at least one sacrificial control surface and at least one primary control surface. The primary control surfaces maintain aircraft controllability in the event that the sacrificial control surface becomes inoperable. | 10-08-2015 |
20150275689 | COMPOSITE FAN CONTAINMENT CASE ASSEMBLY - A fan case for a gas turbine engine includes a composite fan containment case that includes an outer surface. The composite fan containment case includes multiple composite layers that define a generally cylindrical case. An attachment flange extends radially outward from the cylindrical case. The attachment flange comprises a portion of the composite layers. A metallic backing ring is secured to the attachment flange by rivets. | 10-01-2015 |
20150275679 | Abrasive Tip Blade Manufacture Methods - A method is disclosed for manufacturing a blade tip coating. The blade tip coating ( | 10-01-2015 |
20150267618 | GEARED TURBOFAN HIGH GEARBOX POWER DENSITY - A geared architecture for a gas turbine engine includes a central gear supported for rotation about the axis, a plurality of intermediate gears engaged with the central gear and a ring gear circumscribing the intermediate gears. A first flexible coupling is provided between an input shaft driven by a turbine section and the sun gear. The geared architecture provides a power density comprising a power measured in horsepower (HP) related to a weight of the geared architecture within a defined range that benefits overall engine weight and efficiency. | 09-24-2015 |
20150260404 | INTERFACE HEAT SHIELD FOR A COMBUSTOR OF A GAS TURBINE ENGINE - A combustor for a gas turbine engine includes an interface shield between a first heat shield and a second heat shield. | 09-17-2015 |
20150252686 | ROTOR BLADE TIP CLEARANCE - A system includes, in one example, a shroud configured to circumscribe a plurality of rotor blades of a gas rotor engine, and at least one rub button including a head portion having a height configured to extend into a flow path region of the shroud along a central axis of the rub button that extends radially into the flow path region. The head portion includes a profile, orthogonal to the central axis, that varies according to a defined function of the height of the head portion. | 09-10-2015 |
20150252678 | FAN BLADE SPACER - The present disclosure relates generally to a fan blade spacer including a conduit disposed within a fan blade spacer composed of an elastically deformable material. | 09-10-2015 |
20150252672 | RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME - In one exemplary embodiment, an epicyclic gear train for a turbine engine includes a first shaft that is rotatable about an axis. A ring gear includes first and second portions each having an inner periphery with teeth. The first and second portions are secured to one another at a radial interface. At least one of the first and second portions includes a flange that extends radially outward. The flange is fixed to the first shaft in an axial direction by a fastening element. A carrier supports star gears that mesh with the ring gear. A sun gear meshes with the star gears and is coupled to a second shaft. | 09-10-2015 |
20150251774 | ENGINE INSTALLATION SYSTEM - An engine installation system includes two aftward members and two forward members. Each member is connected to a different bootstrap on one end and has a pivotable connection to a pylon on the other end. There is a link that connects one forward member with one aftward member, and another link that connects the other forward member with the other aftward member. There is a variable-length member connected to the bootstrap-end of each of the two aftward members, with each of the variable-length members having a pivotable connection to the pylon. | 09-10-2015 |
20150251242 | Casting Cores and Manufacture Methods - A casting core assembly ( | 09-10-2015 |
20150247458 | BEARING SUPPORT STIFFNESS CONTROL - A bearing support bracket for supporting the bearing assembly includes individually adjustable features for defining and enabling a desired stiffness. | 09-03-2015 |