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| Number | Title | Issue Date |
| 8184909 | Method for comparing sectioned geometric data representations for selected objects A method for comparing a plurality of geometrical data representations each representing a spatial boundary surface of a corresponding geometrical object which surface changes over a selected extent of the object bounded thereby through providing the plurality of ge... | 05/22/2012 |
| 8182905 | Ceramic matrix laminates The invention provides systems and methods for forming low density ceramic felt material cores which are sandwiched between ceramic matrix composites to form a ceramic matrix laminate possessing a high strength-to-density ratio while maintaining a stiffness required... | 05/22/2012 |
| 8182881 | Methods for reducing stress when applying coatings, processes for applying the same and their coated articles A process for applying a coating to an axially split component includes the steps of installing at least one expansion or contraction device to at least one half of an axially split component; expanding at least one half to change a radius and maintain a constant cu... | 05/22/2012 |
| 8181965 | Replaceable brush seal elements The present invention relates to replaceable brush seal assemblies for use with turbines such as industrial gas turbines. In accordance with the present invention, a brush seal assembly comprises a flange, a brush seal mounted to the flange, and retainers preventing... | 05/22/2012 |
| 8181746 | Continuous supply fluid reservoir An assembly for holding a fluid includes an auxiliary reservoir inside a main reservoir. The auxiliary reservoir includes an auxiliary reservoir shell with a fill passage at or near its bottom. The auxiliary reservoir shell also has a vent passage at or near its top... | 05/22/2012 |
| 8181467 | Mid-turbine frame torque box having a concave surface A single point load structure transfers a first load from a first bearing cone and a second load from a second bearing cone of a gas turbine engine to a plurality of struts. The single point load structure includes a stem, a branch connected to the stem and a torque... | 05/22/2012 |
| 8181466 | Mid-turbine frame A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load shell structure and a plurality of struts... | 05/22/2012 |
| 8181441 | Controlled fan stream flow bypass A turbine engine component of a turbofan engine fitted with a bypass air valve includes at least one turbine engine component having a surface with at least one aperture, said turbine engine component located from between a bypass fan duct and a turbine exhaust nozz... | 05/22/2012 |
| 8181346 | System for forming a labyrinth seal on a turbine blade A system for forming a labyrinth seal on a turbine blade has a fixture with a plurality of nozzles for distributing a coolant, a first jaw set for clamping and holding a root portion of the turbine blade in a first orientation, which first jaw set is attached to the... | 05/22/2012 |
| 8177884 | Fuel deoxygenator with porous support plate A device for use in a fluid system includes a fuel channel for receiving fuel having dissolved gas therein. A gas permeable membrane supported by a porous support, the gas permeable membrane in communication with the fuel channel. A gas-removal channel adjacent the ... | 05/15/2012 |
| 8177507 | Triangular serpentine cooling channels A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and cooling channels ex... | 05/15/2012 |
| 8177506 | Microcircuit cooling with an aspect ratio of unity A turbine engine component having improved cooling is provided. The turbine engine component includes an airfoil portion having a leading edge, a trailing edge, a pressure side, a suction side, a root, and a tip, and at least one cooling circuit in a wall of the air... | 05/15/2012 |
| 8177503 | Turbine engine rotating cavity anti-vortex cascade A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade ... | 05/15/2012 |
| 8177494 | Buried casing treatment strip for a gas turbine engine A multiple of circumferential grooves within said arcuate engine casing and an abradable material located radial inboard of the multiple of circumferential grooves. ... | 05/15/2012 |
| 8177492 | Passage obstruction for improved inlet coolant filling A cooled gas turbine engine component includes a cooling passage, one or more cooling inlet apertures in flow communication with a coolant supply and a first end of the cooling passage, and a coolant flow obstruction inside the cooling passage between the one or mor... | 05/15/2012 |
| 8176725 | Reversed-flow core for a turbofan with a fan drive gear system A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and... | 05/15/2012 |
| 8173218 | Method of spraying a turbine engine component A method of spraying a component involves disposing a component near a spray coating device. The component has a first mating feature that is formed as part of the component. A first mask is disposed over a portion of the component and has a second mating feature. T... | 05/08/2012 |
| 8172716 | Epicyclic gear system with superfinished journal bearing An epicyclic gear assembly includes a ring gear, a sun gear, at least one star gear enmeshed between the ring gear and sun gear, a carrier and a journal bearing. The carrier is disposed adjacent the rotatable sun gear and star gear. The journal bearing is disposed i... | 05/08/2012 |
| 8172533 | Turbine blade internal cooling configuration A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cool... | 05/08/2012 |
| 8171978 | Castings, casting cores, and methods The pattern has a pattern material and a casting core combination. The pattern material has an airfoil. The casting core combination is at least partially embedded in the pattern material. The casting core combination comprises a metallic casting core and at least o... | 05/08/2012 |
| 8168117 | Method to improve stability of burn-resistant titanium alloy A powder metallurgy method includes the steps of forming a member, such as a work piece or an aerospace component, from a titanium alloy powder. The average size of a carbide phase in the titanium alloy powder is controlled in order to control an average size of a c... | 05/01/2012 |
| 8167567 | Gas turbine engine airfoil A rotor blade for a gas turbine engine includes an airfoil that extends in span between a root and a tip region. A leading edge and a trailing edge of the airfoil section extend between a chord line of the airfoil. A sweep angle is defined at the leading edge of the... | 05/01/2012 |
| 8167551 | Gas turbine engine with 2.5 bleed duct core case section A core case section for a gas turbine engine a multitude of discreet radial extending 2.5 bleed ducts defined in part by a rear structural wall. ... | 05/01/2012 |
| 8167547 | Gas turbine engine with canted pocket and canted knife edge seal A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a control pocket defined between a radially inner surface and... | 05/01/2012 |
| 8167546 | Ceramic turbine shroud support A turbine shroud includes a ceramic shroud ring configured to surround a plurality of turbine rotor blades, a plurality of slots circumferentially distributed around the ceramic shroud ring, a forward metallic support ring, a plurality of tabs attached to a forward ... | 05/01/2012 |
| 8167314 | Distortion resistant face seal counterface system According to the present invention, an annular face seal arrangement for a gas turbine engine is provided that includes a mounting ring, a mounting member, a rotor, and a stator. The mounting ring has a width extending between a first axial end and a second axial en... | 05/01/2012 |
| 8167237 | Mounting system for a gas turbine engine A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage assembly reacts at least a thrust load. The tangential link reacts at least a... | 05/01/2012 |
| 8166764 | Flow sleeve impingement cooling using a plenum ring A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a plenum ring. The flow sleeve surrounds the combustor liner to form an annulus radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows ... | 05/01/2012 |
| 8162615 | Split disk assembly for a gas turbine engine A split disk assembly for a gas turbine engine includes a forward disk section and an aft disk section, the aft disk section engageable with the forward disk section to retain a multitude of rotor blades therebetween. ... | 04/24/2012 |
| 8162605 | Gas turbine engine case A case for a gas turbine engine includes a single-piece case that includes a combustor case portion and a turbine case portion that is integrally formed with the combustor case portion as one piece. In one example, the single-piece case includes a transition duct/mi... | 04/24/2012 |
| 8161726 | Cooling exchanger duct A method for using a heat exchange system in operating equipment in which a working fluid is utilized in providing selected operations thereof, including for use in lubricating systems for aircraft turbofan engine equipment, the heat exchange system for providing ai... | 04/24/2012 |
| 8159118 | Electron gun An electron gun includes the following: a primary thermionic electron source, a secondary thermionic electron source and a focusing electrode disposed within a first housing that includes one or more reference members adjustably attached to a housing support connect... | 04/17/2012 |
| 8157527 | Airfoil with tapered radial cooling passage A turbine engine airfoil includes an airfoil structure having an exterior surface and an end portion. A cooling passage extends a length radially within the structure in a direction toward the end portion. The cooling passage provides a convection surface along the ... | 04/17/2012 |
| 8153922 | Insert weld repair A method of repairing an aperture and adjacent defect in a part which is started by removing one or more defects adjacent an aperture in a base material. The material is removed to create a weld seam that extends past an area of high stress concentration on the aper... | 04/10/2012 |
| 8152469 | Annular turbine ring rotor A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which... | 04/10/2012 |
| 8152468 | Divoted airfoil baffle having aimed cooling holes A baffle insert for an internally cooled airfoil comprises a liner, a divoted segment and a plurality of cooling holes. The liner has a continuous perimeter formed to shape a hollow body having a first end and a second end. The divoted segment of the hollow body is ... | 04/10/2012 |
| 8151551 | Variable area fan nozzle thrust reverser A nozzle for use in a gas turbine engine includes nozzle doors coupled with a fan nacelle wherein the nozzle doors move in unison between a plurality of positions to influence a bypass airflow through a fan bypass passage. A linkage connects the nozzle doors and an ... | 04/10/2012 |
| 8151458 | Non-metallic cover for a fixture An assembly includes a fixture including an opening shaped to receive a portion of a turbine engine component. A non-metallic cover is placed over at least a portion of the fixture. The cover facilitates reducing metal to metal contact of the fixture and the turbine... | 04/10/2012 |
| 8147982 | Porous protective coating for turbine engine components A method for coating a substrate of a turbine engine component, the method comprising cold spray depositing a metal-based material onto a surface of the substrate, and heating the deposited metal-based material to increase the porosity of the deposited metal-based m... | 04/03/2012 |
| 8147749 | Superalloy compositions, articles, and methods of manufacture A composition of matter comprises, in combination, in weight percent: a largest content of nickel; at least 16.0 percent cobalt; and at least 3.0 percent tantalum. The composition may be used in power metallurgical processes to form turbine engine turbine disks.... | 04/03/2012 |
