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| Number | Title | Issue Date |
| 8136361 | Methods and apparatus for assembling a low noise ejector motive nozzle A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. Th... | 03/20/2012 |
| 8033118 | Bleed airflow balancing control using simplified sensing A simplified air bleed balancing control system for a pair of aircraft gas turbine engines reduces the number of pressure transducers and differential pressure transducers. Advantages include lower weight, less expensive system, better total system MTBF (mean time b... | 10/11/2011 |
| 8015824 | Method and system for regulating a cooling fluid within a turbomachine in real time A method and system for regulating a cooling fluid within a turbomachine in real time. The system may an external flow conditioning system for adjusting at least one property of the cooling fluid, wherein the external flow conditioning system comprises an inlet port... | 09/13/2011 |
| 7997084 | Hybrid power system and method of operating the same A gasifying furnace gasifies solid fuel or liquid fuel. A gas turbine drives a turbine to generate power by using combustion gas generated by burning mixed gas of compressed air compressed in a compressor and gas generated in the gasifying furnace in a combustor. A ... | 08/16/2011 |
| 7942009 | Gas turbine engine with an air cooled bearing A small gas turbine engine with a compressor, a combustor, and a turbine located downstream of the combustor. The compressor and turbine are supported on a rotary shaft, and a main bearing is support on the rotary shaft, the main bearing being located in a hot zone ... | 05/17/2011 |
| 7926289 | Dual interstage cooled engine A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to pro... | 04/19/2011 |
| 7921652 | Aeroengine bleed valve A bleed valve (30) for a gas turbine engine (10) comprises a diffuser (50), through which heated compressor bleed air flows (54) into a bypass duct (22) air stream (B), has a plurality of small holes (40). The plurality of h... | 04/12/2011 |
| 7921653 | Internal manifold air extraction system for IGCC combustor and method A combustor for a turbine including a combustor liner; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween, the first flow sleeve having at least one cooling aperture formed about a circumference thereof for directing compresso... | 04/12/2011 |
| 7870742 | Interstage cooled turbine engine A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a... | 01/18/2011 |
| 7870743 | Compound nozzle cooled engine A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compres... | 01/18/2011 |
| 7841185 | Turbine engine and a method of operating a turbine engine Disparities between optimum engine thrust for aircraft operation and power necessary to drive an ancillary machine such an electrical power generator can cause problems within a turbine engine. Clearly, it is necessary to continue developing sufficient electrical po... | 11/30/2010 |
| 7823389 | Compound clearance control engine A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to t... | 11/02/2010 |
| 7818970 | Controlling a gas turbine engine with a transient load A technique is provided for operating a gas turbine engine that has a combustor with a primary stage and one or more other stages and a first compressor providing an air flow to the combustor. This technique includes driving a variable load device with the rotating ... | 10/26/2010 |
| 7743613 | Compound turbine cooled engine A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a row of nozzle vanes followed by a row of rotor blades. The vanes and blades have corresponding forward and aft internal cooling chann... | 06/29/2010 |
| 7673459 | System and method for providing air to a compressor of an aircraft auxiliary gas turbine engine A system for providing air to a compressor of an auxiliary gas turbine engine of an aircraft. A system turbine has an inlet adapted to receive compressed air from the aircraft. A system compressor is mechanically coupled to the system turbine and has an inlet adapte... | 03/09/2010 |
| 7654094 | Radial turbine and method of cooling nozzle of the same A turbine nozzle (2) that, among components constructing a turbine, reaches particularly high temperature is efficiently cooled with a relatively simple structure. A double casing structure in which a turbine casing (7) is provided outside a turbine sh... | 02/02/2010 |
| 7596954 | Blade clearance control A turbine engine has a circumferentially segmented shroud within a case structure. Each shroud segment is mounted for movement between an inboard position and an outboard position. One or more springs bias the shroud segments toward their inboard positions. One or m... | 10/06/2009 |
| 7584618 | Controlling air flow to a turbine shroud for thermal control A system for controlling a flow of air applied to a gas turbine shroud in an airplane engine, the air flow being adjusted by a regulator valve of position that is controlled by a first control signal calculated on the basis of a first setpoint value corresponding to... | 09/08/2009 |
| 7536864 | Variable motive nozzle ejector for use with turbine engines A gas turbine engine system. The system includes a compressor with a first compressor stage and a second compressor stage, a turbine with a first turbine stage and a second turbine stage, a first flow path connecting the first compressor stage and the first turbine ... | 05/26/2009 |
| 7503179 | System and method to exhaust spent cooling air of gas turbine engine active clearance control An exemplary thermal air exhaust system includes circumferentially extending exhaust passages to exhaust thermal control air from an annular region between an outer casing and a distribution manifold encircling an axially extending portion of the casing after the th... | 03/17/2009 |
| 7434402 | System for actively controlling compressor clearances Aspects of the invention relate to a system and method for actively controlling compressor clearances in a turbine engine by passing a thermal fluid in heat exchanging relation through a compressor vane carrier. During some operational conditions, such as hot restar... | 10/14/2008 |
| 7424360 | Overspeed control system for gas turbine electric powerplant A turbine overspeed control system for use with a gas turbine engine of a gas turbine electrical powerplant. The overspeed control system preferably comprises a first and second overspeed control subsystem. When an overspeed condition of the gas turbine engine is de... | 09/09/2008 |
| 7383686 | Secondary flow, high pressure turbine module cooling air system for recuperated gas turbine engines A secondary flow, turbine cooling air system for the uniform cooling of high pressure turbine module components such as the turbine shroud, turbine blade tips, turbine nozzle, transion liner, and turbine bearing support housing in a recuperated gas turbine engine is... | 06/10/2008 |
| 7383167 | Methods and systems for modeling power plants A modular method of modeling a power plant includes selecting a major component module model from a library of component module models for each major component of the power plant, with each major component module representing a power plant major component of a uniqu... | 06/03/2008 |
| 7377115 | Approach to extending life of gas turbine engine Methods of increasing lifetimes of components in a gas turbine engine. Ordinarily, components are replaced after they experience a certain number of thermal cycles, or a certain operating temperature limit is exceeded. Under one form of the invention, the components... | 05/27/2008 |
| 7367194 | Pulse detonation engine system for driving turbine A pulse detonation engine system (1) for driving a turbine is comprises a detonation generator section (5) including a detonation tube (7) having a tubular hollow section for permitting detonation to be generated therein during combustion stage ... | 05/06/2008 |
| 7360364 | Method and apparatus for assembling gas turbine engine combustors A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein the outer liner is fabricated from a plurality of panels coupled toge... | 04/22/2008 |
| 7353654 | Method and apparatus for achieving power augmentation in gas turbines using wet compression A gas turbine unit and method of operation thereof are disclosed. A very quick and easily controllable augmentation or reduction of shaft power produced by the gas turbine unit, in particular of large gas turbine units exhibiting a pressure ratio larger than 15 bar,... | 04/08/2008 |
| 7353656 | Method and apparatus for achieving power augmentation in gas turbines using wet compression A gas turbine unit and method of operation thereof are disclosed. A very quick and easily controllable augmentation or reduction of shaft power produced by the gas turbine unit, in particular of large gas turbine units exhibiting a pressure ratio larger than 15 bar,... | 04/08/2008 |
| 7353655 | Method and apparatus for achieving power augmentation in gas turbine using wet compression A gas turbine unit as well as a method for operating a gas turbine with high-pressure turbine and a low-pressure turbine unit are disclosed. A very quick and at the same time easily controllable augmentation or reduction of the shaft power of the gas turbine unit ca... | 04/08/2008 |
| 7350358 | Exit duct of annular reverse flow combustor and method of making the same A gas turbine engine comprising an annular reverse-flow combustor having a sheet metal combustor wall between a long exit duct portion and a small exit duct portion of the combustor. An exit duct portion of the combustor forms a sliding joint with a downstream turbi... | 04/01/2008 |
| 7337605 | Thermal management for aircraft auxiliary power unit compartment An improved passive cooling system for an aircraft APU compartment that includes a lightweight annular air-cooled oil cooler that is strategically oriented and shrouded to face its annular inlet away axially downstream from the exhaust of the APU to make it inherent... | 03/04/2008 |
| 7334427 | Ejector with tapered nozzle and tapered needle In an ejector, a nozzle includes a nozzle tapered section having an inner passage with a radial dimension reduced toward a nozzle outlet port, and a needle having a needle tapered section disposed in the inner passage. The needle tapered section has a cross sectiona... | 02/26/2008 |
| 7331763 | Turbine disk A gas turbine section of a gas turbine engine, including a first stage turbine disk, a forward outer seal carried on the turbine disk and a forward shaft cooperating with the first stage turbine disk for transmitting torque generated by the turbine section to a comp... | 02/19/2008 |
| 7329084 | Turbomachine Suitable means for driving a flow are arranged in annular or ring-segment-shaped cavities that are formed in particular in multi-shell casings of turbomachines. Arranged inside the cavity are ejectors that are supplied via suitable means with a motive-fluid flow whi... | 02/12/2008 |
| 7322203 | Device for supplying preconditioned air to an aircraft on the ground A device (10) for supplying preconditioned air to an aircraft on the ground, comprises a compressed air inlet (16) and a compressed air hose (34) having a first end connected to the compressed air inlet (16) and an opposite second end for... | 01/29/2008 |
| 7287384 | Bearing chamber pressurization system A method and device for improved pressure balancing in a bearing chamber pressurization system for gas turbine engines employ a partition member to substantially separate first and second air-oil seals of the bearing housing. ... | 10/30/2007 |
| 7278475 | Control arrangement for cooling power electronic components A control arrangement (10) comprises a first selectable controller (12) for controlling an action, and a second selectable controller (14) for controlling the action. The arrangement also includes a selector (22) for selecting one of the ... | 10/09/2007 |
| 7269955 | Methods and apparatus for maintaining rotor assembly tip clearances A method of operating a gas turbine engine is provided. The gas turbine engine includes at least one engine casing and at least one rotor assembly. The method includes directing airflow through a supply pipe and into a heat exchanger, lowering the temperature of the... | 09/18/2007 |
| 7269956 | Device for utilizing the waste heat of compressors An intercooler (3) is provided with heat exchanger surfaces (6) and is arranged in the gas stream between two compressors (1, 2) or two compressor stage groups for compressing a gas. An aftercooler (5) is also provided with heat exchanger... | 09/18/2007 |
