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| Number | Title | Issue Date |
| 7421853 | Enhanced manual start/stop sequencing controls for a stream turbine powered chiller unit A control system and method for interactive startup and shutdown of a steam turbine driven chiller unit is provided. The chiller unit includes an integrated central control panel to control operation of both the steam turbine system and the refrigerant system. The c... | 09/09/2008 |
| 7421854 | Automatic start/stop sequencing controls for a steam turbine powered chiller unit A control system and method are provided for the automatic startup and shutdown of a steam turbine driven chiller unit. The chiller unit includes an integrated central control panel to control operation of both the steam turbine system and the refrigerant system. Th... | 09/09/2008 |
| 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 |
| 7286923 | System and method for estimating turbine engine deterioration rate with noisy data A method for monitoring engine performance includes sampling exhaust gas temperature associated with a turbine engine over an interval of operational time of the turbine engine. The method further includes applying a first test to identify statistical outliers on th... | 10/23/2007 |
| 7100378 | Method and apparatus for controlling fuel flow to an engine A method for selectively interrupting fuel flow to an engine. The method comprises: in a normal mode, enabling a normal interruption signal for interrupting the fuel flow in response to a normal shutdown signal; and in an emergency mode, enabling an emergency interr... | 09/05/2006 |
| 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 |
| 7043896 | Method and apparatus for controlling fuel flow to an engine An engine shutdown device for controlling a fuel shut-off valve to thereby selectively interrupt fuel flow to an engine. The device comprises a normal switch connected to the fuel shut-off valve and configured to respond to at least one of a normal shutdown signal a... | 05/16/2006 |
| 7011498 | Optimization method for power generation systems Apparatus for controlling the power output efficiency of a power generation system based on an operator input. A processor is coupled to the input means and (i) receives the generated operator command, (ii) receives a plurality of detected ambient air conditions, (i... | 03/14/2006 |
| 6941217 | Microprocessor-based control system for gas turbine electric powerplant A microprocessor-based control system for a gas turbine electrical powerplant. the microprocessor-based control system controls the startup, operation, and shutdown of the gas turbine electric powerplant. The microprocessor-based control system of the present invent... | 09/06/2005 |
| 6789000 | Microprocessor-based control system for gas turbine electric powerplant A microprocessor-based control system for a gas turbine electrical powerplant the microprocessor-based control system controls the startup, operation, and shutdown of the gas turbine electric powerplant. The microprocessor-based control system of the present inventi... | 09/07/2004 |
| 6771501 | Fire resistant electronic engine controller An electronic engine controller is provided in which a backup controller or independent protection module is located in a sealed housing 8 which itself is located within the main housing 4 of the controller. The backup controller is thermally insulated... | 08/03/2004 |
| 6712314 | Method for the control of aero gas turbine engines The exchange, removal or addition, as applicable, of media and/or power is provided between the individual shafts of an engine, between individual engines and between the engines and the aircraft. Thus, additional degrees of freedom are provided, enabling engine par... | 03/30/2004 |
| 6591603 | Pintle injector rocket with expansion-deflection nozzle The present invention provides a rocket engine (10) that is self-compensating on nozzle thrust coefficient for varying ambient backpressures. The rocket engine (10) includes a combustion chamber (12) having an injector end (14) and a nozzle end (16). A pr... | 07/15/2003 |
| 6434473 | Gas turbine aeroengine control system In a control system for a gas turbine aeroengine having a control unit made up of an electronic control unit (ECU) which calculates a fuel flow rate command value based at least on the detected rotational speed of the turbine and the desired power output ... | 08/13/2002 |
| 6353790 | Gas turbine aeroengine control system In a control system for a gas turbine aero engine, the control system (ECU) is configured as a dual control system comprising two channels, Ch-A and Ch-B. Ch-A has two CPUs which conduct calculations separately based on the sensor outputs and one of the C... | 03/05/2002 |
| 5303545 | Pressure based close loop thrust control in a turbofan engine Fuel flow and nozzle area are controlled by a multi-variable control. A requested fan speed is compared with measured fan speed, producing an error signal which is translated in a proportional-integral inner control loop into a requested compressor pressu... | 04/19/1994 |
| 5269136 | Sub-idle stability enhancement and rotating stall recovery In an aircraft gas turbine engine having a variable area exhaust, gas turbine compressor operating conditions are sensed to determine a sub-idle condition or a rotating stall. The exhaust area is increased to a maximum when a sub-idle condition is present... | 12/14/1993 |
| 5259188 | Method and system to increase stall margin A method and system are provided to bias a control subsystem of a gas turbine engine having a fan and compressor. The method includes the steps of measuring an operating parameter of the engine and differentiating this parameter over time to obtain a deri... | 11/09/1993 |
| 4414807 | Method and apparatus for controlling a gas turbine engine A gas turbine engine control for an engine which experiences airflow distortion at the engine inlet face plane uses a static pressure measurement upstream of the face plane along with a corrected rotor speed to generate a signal indicative of the average ... | 11/15/1983 |
| 4294069 | Exhaust nozzle control and core engine fuel control for turbofan engine This control serves to optimize thrust during steady state and transient operation modes of a turbofan engine of the mixed flow type by adjusting or trimming the exhaust nozzle area as a function of fan pressure ratio and fan rotor speed and by adjusting ... | 10/13/1981 |
| 4258545 | Optimal control for a gas turbine engine A method and apparatus for optimally controlling a gas turbine engine utilizes feedback signals each of which is a function of a plurality of output variables. Control signals are generated and transmitted to actuators which vary engine control variables ... | 03/31/1981 |
| 4242864 | Integrated control system for a gas turbine engine An integrated control system for a gas turbine engine of the turbofan type receives signals from a plurality of engine sensors and from the engine operator and generates control signals therefrom. A first control signal regulates the fan exhaust nozzle ar... | 01/06/1981 |
| 3936226 | Control system for variable pitch fan propulsor with reverse pitch A coordinated fan pitch, fuel flow and fan exhaust nozzle area control for a gas turbine powered aircraft propulsor of the bypass duct, variable pitch and exhaust nozzle configuration serves to effectuate reverse pitch change through feather, by minimizin... | 02/03/1976 |
| 3932058 | Control system for variable pitch fan propulsor A control for a variable pitch fan propulsor driven by a turbine type of power plant which fan is mounted in an engine bypass duct having a variable exit nozzle. The control serves to coordinate the control of fuel flow to the engine, the area of the fan ... | 01/13/1976 |
