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| Number | Title | Issue Date |
| 7784263 | Method for determining sensor locations A method for determining sensor locations in a gas turbine engine is provided. The said method includes providing a turbine rear frame including a radially inner surface, a radially outer surface and a plurality of circumferentially-spaced struts extending between t... | 08/31/2010 |
| 7594386 | Apparatus for the prevention of critical process variable excursions in one or more turbomachines Many variables in processes such as those using turbocompressors and turbines must be limited or constrained. Limit control loops are provided for the purpose of limiting these variables. By using a combination of closed loop and open loop limit control schemes, exc... | 09/29/2009 |
| 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 |
| 7290403 | Method and installation for energy production by means of a gas turbine associated with an air separation unit A method which include an air intake into an air separation unit; extracting from the separation unit at least a gas stream, essentially consisting of an air gas, in particular oxygen or nitrogen, and directing one or more of these gas streams towards the combustion... | 11/06/2007 |
| 7243042 | Engine component life monitoring system and method for determining remaining useful component life The claimed invention is a method for determining a relationship between a metal temperature of a turbine component and an operating condition of a turbine housing the component. The claimed invention is also a method for determining consumed operating life for a tu... | 07/10/2007 |
| 7210297 | Method and apparatus for identification of hot and cold chambers in a gas turbine combustor A method for identifying combustion characteristics of a plurality combustion chambers in a gas turbine, the method including: supplying fuel to the combustion chambers at a predetermined fuel rate; sensing combustion dynamic pressure in said plurality of combustion... | 05/01/2007 |
| 7194382 | Systems and methods for detection of combustor stability margin The present invention comprises systems and methods for determining stability margin of a combustor. One embodiment of the present invention includes the steps of providing a measuring device in communication with the combustor, wherein the measuring device generate... | 03/20/2007 |
| 7155897 | Combustion temperature high speed detection device A combustion temperature high speed detection device is provided with a phase lead processing portion, thereby canceling out a detection lag of a temperature detector, and detecting the combustion gas temperature of a combustor at a high speed. The combustion temper... | 01/02/2007 |
| 7140186 | Method and apparatus for monitoring the performance of a gas turbine system A method for monitoring performance of a gas turbine system comprises providing a plurality of combustor cans; placing a plurality of temperature sensors circumferentially around an exhaust plane of the plurality of combustor cans; operating the plurality of combust... | 11/28/2006 |
| 7096669 | Method and apparatus for the prevention of critical process variable excursions in one or more turbomachines Many variables in processes such as those using turbocompressors and turbines must be limited or constrained. Limit control loops are provided for the purpose of limiting these variables. By using a combination of closed loop and open loop limit control schemes, exc... | 08/29/2006 |
| 7089746 | Systems and methods for detection of blowout precursors in combustors The present invention comprises systems and methods for detecting flame blowout precursors in combustors. The blowout precursor detection system comprises a combustor, a pressure measuring device, and blowout precursor detection unit. A combustion controller may als... | 08/15/2006 |
| 7065471 | Method and system for diagnosing state of gas turbine An operation monitoring unit 11 for acquiring process data from sensors 10 installed to a gas turbine and operation information of the gas turbine; communication units 12, 14 for transmitting each of said two kinds of data on the gas turbine acq... | 06/20/2006 |
| 7028461 | Uniaxial gas turbine system A uniaxial gas turbine system, comprising a uniaxial gas turbine, a rotary machine driven by the uniaxial gas turbine, a continuously variable transmission for transmitting a driving force from the uniaxial gas turbine to the rotary machine, and a control device for... | 04/18/2006 |
| 6979118 | Estimating combustor flame temperature based on frequency of combustor dynamics transverse mode A method of determining the temperature inside a combustion liner without making a direct measurement of the actual temperature. The technique is based on a measurement of the frequency of one of the transverse acoustic modes occurring inside the combustion chamber.... | 12/27/2005 |
| 6962043 | Method and apparatus for monitoring the performance of a gas turbine system A method for monitoring performance of a gas turbine system comprises providing a plurality of combustor cans; placing a plurality of temperature sensors circumferentially around an exhaust plane of the plurality of combustor cans; operating the plurality of combust... | 11/08/2005 |
| 6463730 | Valve control logic for gas turbine recuperator Control logic and a method for controlling turbine speed. In an embodiment, the inventive control logic controls turbine speed of turbine generators operating in a stand-alone mode and/or a grid mode.... | 10/15/2002 |
| 6269627 | Rapid thrust response control logic for shaft-driven lift fan STOVL engine A short take-off and vertical landing ("STOVL") aircraft has a conventional gas turbine engine that is selectively mechanically connected to a vertically-oriented lift fan by a drive shaft when the aircraft operates in a vertical flight mode. An engine co... | 08/07/2001 |
| 6212871 | Method of operation of a gas turbine engine and a gas turbine engine A gas turbine engine that has a turbine (1) mounted downstream of a combustor (5), a compressor turbine (2) mounted downstream of turbine (1) for producing power for driving a compressor (3), a heat exchanger (6) having a first circuit (61) con... | 04/10/2001 |
| 6202400 | Gas turbine exhaust recirculation method and apparatus To improve the thermal efficiency when an exhaust heat recovery type combined cycle plant having a gas turbine and a steam turbine in combination is operated at a partial load, the gas turbine exhaust is recirculated and returned to the compressor, and th... | 03/20/2001 |
| 6035629 | System for controlling acceleration of a load coupled to a gas turbine engine A system and method of controlling the acceleration of a load driven by a gas turbine engine detects the existence of an overload condition and reduces an acceleration setpoint when such condition arises.... | 03/14/2000 |
| 5857321 | Controller with neural network for estimating gas turbine internal cycle parameters A gas turbine control system includes a controller that is coupled to actuator systems that govern operation of the gas turbine. The controller includes a processor for generating respective actuator control signals in correspondence with a plurality of t... | 01/12/1999 |
| 5855111 | Nitrogen oxide removal control apparatus A power generation plant possessing a gas turbine includes a nitrogen oxide removal apparatus for injecting a reducing material such as ammonia into exhaust gas from the gas turbine to reduce NOx emission under a predetermined level. To a feedback control... | 01/05/1999 |
| 5839268 | Active hydraulic rotor damping The compressor shaft in a gas turbine engine is supported on a bearing having four independently hydraulically pressurized cells. The pressure in the cells is controlled by a signal processor based on engine operating parameters, including stall margin an... | 11/24/1998 |
| 5752379 | Non-recoverable surge and blowout detection in gas turbine engines Indications of non-recoverable compressor surge and blowout are provided by sensing compressor pressure, temperature and speed and comparing exhaust temperature with stored values and successive values depending upon instantaneous compressor speed and its... | 05/19/1998 |
| 5675188 | Adjustable speed gas turbine power generation apparatus and its operation method independent of ambient temperature An adjustable speed gas turbine power generation apparatus can maintain a rated output of the gas turbine generation apparatus irrespective of ambient temperature change. For this purpose, the rotational speed of the secondary winding of the generator is ... | 10/07/1997 |
| 5584172 | Nitrogen oxide removal control apparatus A power generation plant possessing a gas turbine includes a nitrogen oxide removal apparatus for injecting a reducing material such as ammonia into exhaust gas from the gas turbine to reduce NOx emission under a predetermined level. To a feedback control... | 12/17/1996 |
| 5457953 | 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 ... | 10/17/1995 |
| 5424824 | Method and apparatus for normal shock sensing within the focal region of a laser beam A system using Lidar/Laser anemometry for measuring the position of the normal shock wave and air velocity in the inlet of a supersonic engine is described, A laser beam is focused over a region in the inlet where the shock is expected to be. Small partic... | 06/13/1995 |
| 5136841 | Aircraft propulsion control system Integration of engine functions and data communications between an aircraft propulsion module and an airframe is enabled by the use of fiber optic links which multiplex information and control functions without risk of an electrical failure in one portion... | 08/11/1992 |
| 5048285 | Control system for gas turbine engines providing extended engine life A control system for use in gas turbine engines simultaneously provides for improved engine efficiency and extended engine life without sacrificing engine performance. The control system is characterized by both standard and extended engine life (EEL) ope... | 09/17/1991 |
| 5044155 | Aircraft propulsion control system Integration of engine functions and data communications between an aircraft propulsion module and an airframe is enabled by the use of fiber optic links which multiplex information and control functions without risk of an electrical failure in one portion... | 09/03/1991 |
| 5012637 | Method and apparatus for detecting stalls A gas turbine engine control system which receives an engine condition and generates a parameter signal representative of the condition. The control system also receives a temperature signal representative of the engine temperature downstream of the engin... | 05/07/1991 |
| 4991389 | Bleed modulation for transient engine operation A gas turbine engine control system modulates a compressor bleed valve between full open and full closed during transient engine operation as a function of the rate of change of compressor speed biased by flight conditions, such as altitude, and corrected... | 02/12/1991 |
| 4884397 | Control system topping loop A control system, such as for a gas turbine engine, prevents a parameter from exceeding a maximum, steady state limit using a topping loop. The topping loop compares the actual value of the parameter to a transient limit which is initially somewhat lower ... | 12/05/1989 |
| 4875168 | Engine speed control apparatus Apparatus for synchronizing the spool speed between engines of a multi-engine aircraft having, for each engine, an electronic engine control (EEC) with a speed rating logic portion having an engine speed algorithm for calculating an EEC command speed sign... | 10/17/1989 |
| 4845943 | Control method for topping loop A control system, such as for a gas turbine engine, prevents a parameter from exceeding a maximum, steady state limit using a topping loop. The topping loop compares the actual value of the parameter to a transient limit which is initially somewhat lower ... | 07/11/1989 |
| 4251873 | Digital computing apparatus particularly for controlling a gas turbine engine A digital computing apparatus, particularly for use in controlling a gas turbine engine, comprises two identical computing devices each of which is responsive to identical time control signals and to identical input signals, so as to supply nominally iden... | 02/17/1981 |
| 4249238 | Apparatus for sensor failure detection and correction in a gas turbine engine control system An improved gas turbine engine control system maintains a selected level of engine performance despite the failure or abnormal operation of one or more engine parameter sensors. The control system employs a continuously updated engine model which simulate... | 02/03/1981 |
| 4157124 | Vehicular single shaft gas turbine engine power system A vehicular gas turbine engine power system includes an engine, an automatic clutch, a service clutch and an infinitely variable transmission coupled successively along a power train. A vehicle control system controls engine speed, transmission ratio and ... | 06/05/1979 |
| 4053745 | Valve contingency detection system for a turbine power plant A system for detecting the failure of steam inlet valves to respond properly to their respective control signals, is disclosed. The detection of such a contingency provides an appropriate indication, and also initiates a transfer to single valve operation... | 10/11/1977 |
