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| Number | Title | Issue Date |
| 8069672 | Method and systems for operating a combined cycle power plant An embodiment of the present invention may provide a variable speed booster, which receives air from a compressor of a gas turbine through an intercooler, to supply air at a relatively constant pressure to an air processing unit. An embodiment of the present inventi... | 12/06/2011 |
| 7980083 | Method and system for operating a combined cycle power plant An embodiment of the present invention may provide a variable speed booster, which receives air from a compressor of a gas turbine through an intercooler, to supply air at a relatively constant pressure to an air processing unit. An embodiment of the present inventi... | 07/19/2011 |
| 7975490 | Method and systems for operating a combined cycle power plant A method and system for operating a gas turbine engine power system are provided. The system includes a gas turbine engine system that includes a gas turbine engine coupled to an electrical generator through a first shaft wherein the gas turbine engine includes a co... | 07/12/2011 |
| 7797945 | Bleed valve outlet flow deflector A bleed valve assembly for discharging bleed air into a gas turbine engine bypass plenum includes a bleed flow duct, a bleed valve, and a flow deflector. The bleed flow duct is contoured such that it delivers uniformly flowing bleed air to the flow deflector when th... | 09/21/2010 |
| 7784288 | Methods and systems of variable extraction for compressor protection A method of protecting a turbine compressor of a gas turbine engine that is part of an integrated gasification combined-cycle power generation system that includes an air separation unit that may include the steps of: (1) extracting an amount of compressed air that ... | 08/31/2010 |
| 7726134 | Method and apparatus for performing gas turbine engine maintenance A method for performing maintenance on a gas turbine engine assembly includes unplugging a first connector from a first socket, the first connector electrically coupled to the engine control unit, the first socket electrically coupled to the hydromechanical unit, pl... | 06/01/2010 |
| 7617687 | Methods and systems of variable extraction for gas turbine control A method of controlling a load of a gas turbine engine that is part of an integrated gasification combined-cycle power generation system, which includes an air separation unit, that includes the steps of: (1) extracting an amount of compressed air that is compressed... | 11/17/2009 |
| 7536865 | Method and system for balancing bleed flows from gas turbine engines A bleed air balancing system includes a plurality of bleed air flow paths (12) each carrying bleed air from one of a plurality of gas turbine engines (10), each bleed air flow path (12) including a flow rate sensor (19), and a circuit ( | 05/26/2009 |
| 7387489 | Bleed valve outlet flow deflector A bleed valve assembly for discharging bleed air into a gas turbine engine bypass plenum includes a bleed flow duct, a bleed valve, and a flow deflector. The bleed flow duct is contoured such that it delivers uniformly flowing bleed air to the flow deflector when th... | 06/17/2008 |
| 7334412 | Cooling air and injected liquid system for gas turbine blades The invention relates to a turbine 1, in particular a gas turbine, which along a swivel-mounted rotationally symmetrical rotor 2 has a compressor 3, a combustion chamber 5 and a turbine section 7 formed of a plurality of turbine st... | 02/26/2008 |
| 7258524 | Method of regulating the flow rate of air in a rotary shaft of a turbomachine A device applied to regulating the flow rate of air flowing in a rotary shaft of a turbomachine, the shaft including at least one through orifice for passing air. The device at least one shutter member for shutting the orifice and secured to a deformable blade prese... | 08/21/2007 |
| 7249929 | Bleed housing A gas turbine engine compressor has a number of shroud rings, at least a bleed one of which defines a number of bleed ports. A structural hub is downstream of the shroud rings and secured relative to the shroud rings. A structural hub case extends from an aft joint ... | 07/31/2007 |
| 7246482 | Gas turbine engine bleed air power assist system and method A bleed air power assist system is coupled to a gas turbine engine that includes a high pressure turbine, a low pressure turbine, and an electrical generator driven by the high pressure turbine. The bleed air power assist system selectively bleeds air discharged fro... | 07/24/2007 |
| 7181914 | Diffuser for gas turbine engine A gas turbine engine pre-diffuser 40 is generally annular, including radially inner and radially outer walls 40 and 42 and a generally cylindrical midline 48 defined between the walls. The pre-diffuser 40 includes a central member ... | 02/27/2007 |
| 7184865 | Fault detection logic for engines In a fault detection logic for an engine controller for the detection of too low or too high a thrust relative to an intended positive or negative acceleration, the positive or negative error of the engine pressure ratio and the positive or negative acceleration of ... | 02/27/2007 |
| 7140188 | Gas turbine engine with intake air flow control mechanism A gas turbine engine includes: an air flow control system installed in an air intake path for introducing air to a compressor. The air intake path is located outside and upstream with respect to the compressor. The engine also includes intake air flow control means ... | 11/28/2006 |
| 7124591 | Method for operating a gas turbine A gas turbine includes a compressor, a combustor, a turbine, and a flow path diverting an excess portion of the compressed air produced by the compressor around the turbine. The flow path conducts the excess portion into a turbine exhaust gas flow producing a cooled... | 10/24/2006 |
| 7096667 | Control of gas turbine for catalyst activation A catalytic gas turbine includes a compressor, a catalytic combustor, a turbine, and a flow path conducting a bypass portion of the compressed air around the combustor and turbine. A method of operating the catalytic gas turbine to activate a catalyst in the catalyt... | 08/29/2006 |
| 7069728 | Multi-position BOV actuator A multi-position pressurized fluid actuator is mounted for movement in a casing. The actuator includes at least one selectively openable opening at a location corresponding to an intermediate position through which pressurized fluid can be selectively bled from the ... | 07/04/2006 |
| 7065973 | Stall detection and recovery system A stall detection and recovery system (10) for a gas turbine engine (1) comprises surge detection means (50 for detecting an engine surge and providing a surge detection signal (154) for indicating said engine surge. The system also inclu... | 06/27/2006 |
| 6938404 | Supercharged open cycle gas turbine engine The present invention provides a supercharged open cycle gas turbine engine comprising a core engine for generating shaft power output, a supercharger for increasing the pressure of intake air of the core engine, said supercharger includes a rotary ram-in compressor... | 09/06/2005 |
| 6871487 | System for detecting and compensating for aerodynamic instabilities in turbo-jet engines The present invention relates to a system for detecting aerodynamic instabilities in a jet turbine engine having a pressure transducer mounted in the engine. The pressure transducer, welded to a circuit in signal communication with a controller, is adapted to send m... | 03/29/2005 |
| 6820429 | Adaptive acceleration schedules for gas turbine engine control systems Disclosed is an engine surge avoidance system and method which adapts the acceleration schedules (i.e., P2.5 bleed valve and NDOT) to prevent engine surge events from occurring while minimizing reductions in engine response time. The surge avoidance syste... | 11/23/2004 |
| 6782701 | Master-slave engine bleed flow sharing control method and system A system and method for an engine bleed flow-sharing control system is disclosed. For a multi-engine bleed system, one (10) of the engines is selected as the master channel (15) such that the bleed air supply pressure of the control system receiving th... | 08/31/2004 |
| 6779346 | Control of gas turbine combustion temperature by compressor bleed air A method of operating a combustor in a gas turbine that receives combustion air from a compressor includes a) controlling combustion temperature as a function of compressor discharge air bled from the compressor by determining a minimum amount of compressor discharg... | 08/24/2004 |
| 6755025 | Pneumatic compressor bleed valve A pneumatically operated compressor bleed valve communicating between a compressor housing and a bypass duct of a gas turbine engine. The valve has an annular piston slidably mounted within an annular chamber concentric the longitudinal engine axis. An annular valve... | 06/29/2004 |
| 6701716 | Bleed valve assembly A bleed valve 60 for regulating a fluid flow through a bleed hole 88 defined by a casing 49 of a gas turbine engine 10 compressor 22, the bleed valve 60 comprises a central axis 92, a piston 62 and a static structure 70, the static structure 70 generally ... | 03/09/2004 |
| 6513333 | Surge detection system of gas turbine aeroengine A surge detection system for detecting a surge occurred at a compressor of a gas turbine aeroengine having a turbine connected to the compressor. In the system, the ratio between the compressor outlet pressure and its differential and the differential of ... | 02/04/2003 |
| 6438941 | Bifurcated splitter for variable bleed flow An air bleed assembly for extracting air from a flowpath in a gas turbine engine includes a casing for surrounding a row of circumferentially spaced apart rotor blades and defining at least in part the flowpath for receiving air compressed by the rotor bl... | 08/27/2002 |
| 6314716 | Serial cooling of a combustor for a gas turbine engine A combustor for a gas turbine engine uses compressed air to cool a combustor liner and uses at least a portion of the same compressed air for combustion air. A flow diverting mechanism regulates compressed air flow entering a combustion air plenum feeding... | 11/13/2001 |
| 6195982 | Apparatus and method of active flutter control A system for controlling aeromechanical instability or flutter in turbofan engines having fan blades employs a sensor, such as an off-blade static pressure sensor or proximity detector mounted on a turbofan engine at an inlet of a rotor of the engine for ... | 03/06/2001 |
| 6141951 | Control system for modulating bleed in response to engine usage A control system for operating a compressor bleed valve in a gas turbine engine to prevent compressor operation in surge region determines engine stability in response to a plurality of sensed engine parameters, and calculates and stores engine parameters... | 11/07/2000 |
| 6122905 | Compressor bleed valve A bleed valve is in fluid communication with the compressor fluid flow path and the bypass fluid flow path whereby a piston extends radially of the valve and includes a piston head radially remote from the compressor fluid flow path. A pneumatic chamber s... | 09/26/2000 |
| 6059522 | Compressor stall diagnostics and avoidance A pressure sensor (12) is located in the compressor stage of a gas turbine engine (10) to provide a pressure signal (PR1) that shows the compressor flow characteristics. The pressure signal (PR1) is applied to a bandpass filter (16) with roll-offs above a... | 05/09/2000 |
| 6050079 | Modulated turbine cooling system A modulated flow transfer apparatus for transferring a fluid flow from a static element to a rotor of a gas turbine engine has an annular static inducer for accelerating the fluid flow in a substantially circumferential direction. The inducer has an annul... | 04/18/2000 |
| 5915917 | Compressor stall and surge control using airflow asymmetry measurement A technique for controlling compressor stall and surge is disclosed. In a gas turbine engine, static pressure asymmetry is sensed at a plurality of locations along the circumference of the compressor inlet. Time rate of change of the mass flow in the comp... | 06/29/1999 |
| 5865030 | Gas turbine combustor with liquid fuel wall cooling A gas turbine combustor 1 prevents an inequality of distribution of temperatures at the outlet of the combustor which might otherwise be caused by cooling air introduced into the combustor. A liner 2 having an outer liner 2' and an inner liner 2", is disp... | 02/02/1999 |
| 5775098 | Bypass air valve for a gas turbine A bypass air valve is provided comprising a liner, a strap, and apparatus for selectively actuating the valve. The liner includes an inner surface, an outer surface, a plurality of first regions, and a plurality of second regions. Each first region includ... | 07/07/1998 |
| 5749217 | Low emission combustion system for a gas turbine engine The control systems for reducing NOx in the combustion systems of past gas turbine engines has incorporated a variety of expensive and complicated techniques to reduce the NOx level. For example, such systems use schemes for introducing more air into the ... | 05/12/1998 |
| 5515673 | Device for controlling the opening and closing of discharge valves of a turbojet engine A control device makes it possible to rapidly shift the bleed valves of an aircraft turbojet engine to a large opening position when the engine is under low power operation in order to prevent flame-out. The device allows for instantaneously interrupting ... | 05/14/1996 |
