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| Number | Title | Issue Date |
| 7946107 | Mixture ratio stabilizer for liquid propellant rocket engine There is provided a mixture ratio stabilizer for a liquid propellant rocket engine which comprises: a body internally having a chamber and a fuel supply hole communicating with an end of the chamber to receive fuel from a fuel supply pump, an oxidizer inlet, and a f... | 05/24/2011 |
| 7584602 | Augmentor flow control with thermal recirculation function using augmentor valves A fuel system for a gas turbine engine having at least one augmentor zone which fuel system includes a fuel pump (12) drawing fuel from a fuel tank (10) and pumping the fuel in a downstream direction, at least one fuel line (14) connecting the f... | 09/08/2009 |
| 7493752 | Control system for aircraft engine A control apparatus 50 for a gas turbine engine for an aircraft includes engine control means 52 forming part of an outer fuel control loop and fuel control means/overthrust protector 76 forming part of an inner fuel control loop. Overthrust pro... | 02/24/2009 |
| 7413141 | Gas turbine engine fuel control system and regulating valves therefor A fuel control system for reheat burners of a gas turbine engine has a plurality of metering valves for respective burners, and throttle valves in series with the respective metering valves. A pressure regulating valve is provided for introducing pressurized fuel in... | 08/19/2008 |
| 7331169 | Control logic for fuel controls on APUs Conventional auxiliary power units (APUs) may experience over-temperature shutdowns when attempting to start them at high altitudes. Further, such conventional APUs may also experience overspeed conditions when a generator load is removed during on-speed operations.... | 02/19/2008 |
| 7210653 | Electric-based secondary power system architectures for aircraft Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be co... | 05/01/2007 |
| 7198234 | Method and apparatus for modulating flow separation An apparatus comprising: an aerodynamic surface adapted for producing an adverse pressure gradient in a fluid flow; and a first pulse detonation actuator disposed adjacent the aerodynamic surface and adapted for impulsively detonating a fuel/air mixture to produce a... | 04/03/2007 |
| 7185485 | Method and system for failure accommodation of gas generator fuel metering system An apparatus for providing a backup fuel metering system for the gas generator section (24) of a gas turbine engine (10) is disclosed that includes a gas generator (24) and an augmentor (40). The apparatus includes a gas generator fuel me... | 03/06/2007 |
| 7140175 | Throttle control device in particular for turbine aero engine test bench The invention concerns a throttle control device for an aircraft turbine engine. It comprises a control assembly acting on the native command of the turbine engine (MT1–MT3) as a function of a manual input defined by a pilot control element (1... | 11/28/2006 |
| 7137242 | Fuel system A fuel control system for a staged combustion engine comprising, a fuel metering unit including a fuel metering valve having a fuel metering orifice the opening of which is varied to meter the flow of fuel through the metering valve in use, a fuel staging unit recei... | 11/21/2006 |
| 7082767 | Process and device for supplying the turbojets of an aircraft during automatic flight According to the invention, during level automatic flight of the aircraft (A) at steady altitude, the preset value EPRt, common to all the turbojets (M1 to M4) and corresponding to a particular value of the ratio EPR of the gas pressures at the outlet ... | 08/01/2006 |
| 7080503 | Control system A fuel control system as claimed in claim 1 wherein, the pressure raising valve includes: a pressure raising valve member exposed to fuel pressure within a reference chamber, an inlet to which fuel at supply... | 07/25/2006 |
| 7028480 | Steam temperature control system, method of controlling steam temperature and power plant using the same A steam temperature control system for a power plant for controlling a temperature of steam flowing through steam pipes connected to a heat exchanger to a target temperature by spraying water by means of a spray valve of an attemperator, having a target temperature ... | 04/18/2006 |
| 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 |
| 7003940 | System for control and regulation of the flame temperature for single-shaft gas turbines In order to limit the flame temperature peaks following sudden load variations, corresponding control is planned of the position of the blades (13) of the distributor with variable geometry, of a single-shaft gas turbine (18); in particular, the contro... | 02/28/2006 |
| 7000376 | Gas turbine control system A control system for a gas turbine, wherein a number of regulators generate respective control signals selectable to regulate fuel supply to a combustion chamber of the gas turbine. The regulators include at least one speed/load regulator, wherein a first and a seco... | 02/21/2006 |
| 6935120 | 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... | 08/30/2005 |
| 6931835 | Multivariant set point using N1 and N2 for engine control A method for selecting a setpoint for a turbofan engine having a fan speed and a core idle speed scheduling includes determining a weighting factor based upon a throttle lever position, the weighting factor being zero in an idle region and ranging from zero to one i... | 08/23/2005 |
| 6748744 | Method and apparatus for the engine control of output shaft speed In accordance with one aspect of the present invention, in a control system for controlling a gas turbine engine, there is provided a system and a method for determining an optimized output shaft speed for a required thrust and setting an appropriate engine power. T... | 06/15/2004 |
| 6688097 | Multivariant set point using N1 and N2 for engine control A turbofan engine throttle control system and method for eliminating dead bands in the throttle control by decreasing and increasing the fuel flow to the engine during transition from the scheduled core speed to scheduled fan speed of the engine to effect... | 02/10/2004 |
| 6655126 | Overthrust protection system An overthrust protection system for a gas turbine in which fuel is supplied at a controlled flow rate to a combustor (4) of the gas turbine. The overthrust protection system uses a bypass valve (24) to divert fuel flow away from the combustor (4). The ope... | 12/02/2003 |
| 6487490 | Speed modification system for gas turbine engine to allow trimming of excess The present invention provides a fan speed indication system enabling the operator to control engine rotational speed to match specific thrust performance to flight requirements. The invention accommodates variations in engine thrust performance measured ... | 11/26/2002 |
| 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 |
| 6250602 | Positive shut-off metering valve with axial thread drive Disclosed herein is a fuel/ignitor valve for metering liquid or gaseous fuel having a servo motor-actuated pintle providing rapid flow rate adjustment response and positive flow shut-off. The fuel flows from an inlet port through a venturi passageway havi... | 06/26/2001 |
| 5887419 | Control system for a ducted fan gas turbine engine If the fan of a ducted fan gas turbine engine is damaged, the power output of the engine may not be sufficient for a given throttle setting. The present invention provides a control system which detects fan damage and ensures that there is sufficient fuel... | 03/30/1999 |
| 5806301 | Ramjet/scramjet inlet isolator unstart prevention Pressure sensors are placed at axial locations in the isolator of a scramjet or ramjet. An engine fuel control produces calculated pressure values for the those locations from a stored function. As the engine operates, the pressure signals from the pressu... | 09/15/1998 |
| 5660040 | Scramjet fuel injection system having independent fuel supplies for supersonic and hypersonic operation A fuel injector for a scramjet engine includes independently manifolded normal (48, 54) and axial fuel injection (56). Various construction details are developed that provide effective performance of the fuel injector over a range of speed and combustor c... | 08/26/1997 |
| 5628185 | Gas turbine engine fuel control system A ducted fan gas turbine engine is provided with means for measuring the actual temperature of air exhausted from its high pressure compressor and means for computing a theoretical value of that temperature. The difference between the actual and theoretic... | 05/13/1997 |
| 5622045 | System for detecting and accommodating gas turbine engine fan damage Foreign object ingestion damage detection and accommodation system for a gas turbine engine system having a gas turbine engine with multiple rotating members, such as a twin spool configuration. System includes speed sensors for sensing the rotational spe... | 04/22/1997 |
| 5579632 | Overspeed governor control system A mechanical governor for use in a fuel management system having a fuel metering loop responsive to an electronic computer for supplying fuel to a combustion chamber of a turbine. The mechanical governor includes a cylindrical spinning spool valve assembl... | 12/03/1996 |
| 5544480 | Augmentor light-off improvement The disclosure describes a fuel scheduling system that controls the fuel into the pilot burner of an afterburner by making fuel flow directly proportional to compressor discharge pressure at low compressor pressures, but to limit fuel flow to a fixed valu... | 08/13/1996 |
| 5517819 | Engine full authority digital engine control automatic mach hold An engine controller system maintains a desired mach number for an aircraft. The fan speed of a slave engine is synchronized with the fan speed of a master engine. A previous Mach number value is compared with an actual Mach number value to determine a Ma... | 05/21/1996 |
| 5440490 | Aircraft engine emergency control system In the event of incipient engine speed or loss of normal engine control fuel flow rate in a jet engine is limited by a speed governor. A speed governor arrangement with optionally selectable emergency speed control is described. Maximum engine speed limit... | 08/08/1995 |
| 5394689 | Gas turbine engine control system having integral flight Mach number synthesis method A gas turbine engine digital electronic control is disclosed which is capable of maintaining safe, efficient engine thrust levels in the event of loss of communication with an aircraft flight computer. Specifically, a limited number of engine sensor input... | 03/07/1995 |
| 5345386 | Aircraft engine management system An aircraft jet engine management system has a digital electronic control unit (DECU) which measures turbine blade temperature (TBT) and controls the engine in such a way as not normally to exceed a TBT normal datum, there being an over-ride facility whic... | 09/06/1994 |
| 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 |
| 5285638 | Method and apparatus for maximizing fuel efficiency for jet engines A system and method to maximize fuel efficiency for a plurality of simultaneously operating engines is disclosed. The system includes means to determine the fuel consumption of the engine, measure the thrust of each engine and means to substantially equal... | 02/15/1994 |
| 5272637 | Method and apparatus for controlling the supply of fuel to a gas turbine during load rejection A fuel supply amount is controlled while the load of a gas turbine is changed so that the fuel supply amount is shifted to a fuel supply amount in accordance with the changed load. A fuel supply control valve is operated at high speed during an initial st... | 12/21/1993 |
| 5224343 | Constant fuel supply device for a thruster In a fuel supply system for a space missile or a spacecraft in which the thrusters are supplied with liquid or gaseous fuel from a fuel tank in which the tank pressure decreases continuously during the operational life of the system, the fuel throughput a... | 07/06/1993 |
| 5157918 | Temperature compensating device for turboshaft aero-engines A compensating device for the temperature in front of the high pressure turbine of a compound turboshaft aero-engine which is regulated to a designated constant temperature behind the low pressure turbine is provided with a function generator which suppli... | 10/27/1992 |
