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| Number | Title | Issue Date |
| 8127527 | Methods and systems for operating oxidizer systems A method and system for operating a gas turbine engine is provided. The system includes in serial flow arrangement, at least one compressor, a combustor, and at least one turbine. The method includes compressing atmospheric air in the gas turbine engine, channeling ... | 03/06/2012 |
| 8117827 | Apparatus for operating gas turbine engines A gas turbine engine assembly includes at least one propelling gas turbine engine and an auxiliary engine used for generating power. The propelling gas turbine engine includes a fan assembly and a core engine downstream from said fan assembly. The core engine includ... | 02/21/2012 |
| 8015795 | Aircraft combination engines plural airflow conveyances system An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being a plurality of air transfer ... | 09/13/2011 |
| 7762056 | Aircraft combination engines exhaust thrust recovery A gas turbine engine with a turbine with an exhaust manifold thereabout from which fluids can be transferred to the turbine and an air compressor having an air transfer duct extending therefrom so as to be capable to provide compressed air in that air transfer duct ... | 07/27/2010 |
| 7752834 | Aircraft propulsion systems Disclosed are propulsion systems 30 providing reduced fuel burn, weight and cost. A single gas generator core 38 drives multiple bladed propulsion elements 36 with a power train 48. The core 38 has a forward compressor 56 an... | 07/13/2010 |
| 7721524 | Integrated airbreathing and non-airbreathing engine system An engine assembly includes a gas-turbine engine having a tailcone portion and a bypass duct, a rocket engine combustion assembly located at the tailcone portion of the gas-turbine engine, and a movable nozzle segment subassembly that is selectively engageable with ... | 05/25/2010 |
| 7690188 | Combination engines for aircraft An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being an air transfer duct connect... | 04/06/2010 |
| 7690189 | Aircraft combination engines inlet airflow control system A power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine in an engine compartment in the aircraft with an air inlet in the aircraft that is curved along its extent in leading to an air compressor in the g... | 04/06/2010 |
| 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 |
| 7412831 | Integral cooling system for rotary engine A rotary combustion engine (12) with a self-cooling system comprises a heat exchanging interface for discharging excess heat from the rotary combustion engine (12), and a direct drive fan (44) integrated on the rotary engine output shaft (26 | 08/19/2008 |
| 7231770 | Onboard supplemental power system at varying high altitudes Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a super... | 06/19/2007 |
| 7228683 | Methods and apparatus for generating gas turbine engine thrust using a pulse detonator Methods and apparatus for generating thrust from a gas turbine engine using a pulse detonation system is provided. The gas turbine engine includes a fan assembly, and a bypass duct channeling air to a core engine and the pulse detonation system. The method includes ... | 06/12/2007 |
| 7219490 | Nested core gas turbine engine A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section. ... | 05/22/2007 |
| 7178338 | Variable area nozzle An exhaust nozzle assembly for a gas turbine engine, the assembly comprises a main axis, an inner nozzle, an outer nozzle, a translatable centre-body and an actuator for translating the centre-body between a forward position and a rearward position. The centre-body ... | 02/20/2007 |
| 7121078 | Methods and apparatus for operating gas turbine engines A method facilitates assembling a gas turbine engine assembly. The method comprises providing at least one propelling gas turbine engine that includes a core engine including at least one turbine. The method also comprises coupling an auxiliary engine to the propell... | 10/17/2006 |
| 7111462 | Onboard supplemental power system at varying high altitudes Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a super... | 09/26/2006 |
| 7107755 | Engine arrangement An engine arrangement (14) comprises a gas turbine engine unit (16) and first and second support members (18, 20) extend from a structural component (24) of the engine casing (22) to support the engine unit in a position spaced fro... | 09/19/2006 |
| 7107757 | Aircraft provided with thrust reversers Some but not all engines of an aircraft are provided with thrust reversers. A safety device disables, at least from the position corresponding to idling, the action of the throttles corresponding to the engines devoid of thrust reversers when the thrust reversers ar... | 09/19/2006 |
| 7107756 | Turbofan arrangement A bypass turbofan engine comprises a first propulsion system and a second propulsion system. The first propulsion system comprises a first fan rotor, a core engine, a first low pressure turbine and a first fan shaft drivingly connecting the first turbine and the fir... | 09/19/2006 |
| 7089744 | Onboard supplemental power system at varying high altitudes Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a super... | 08/15/2006 |
| 7059458 | Device for damping the displacement of a part, involving a metal wire A damping device used for motor vehicle safety, for damping the displacement of at least one part set in motion during a collision between a motor vehicle and an external object, the part being, for example, a bumper, a steering column or a bonnet of a motor vehicle... | 06/13/2006 |
| 6981364 | Combine engine for single-stage spacecraft A novel combined engine for a single-stage spacecraft is provided that combines a air-breathing engine utilizing oxygen in the atmosphere as oxidizer and rocket engines for obtaining thrust outside the atmosphere and that does not require a portion whose shape is va... | 01/03/2006 |
| 6968674 | Methods and apparatus for operating gas turbine engines A method facilitates operating a gas turbine engine assembly including a propelling engine and an auxiliary power engine. The method comprises channeling a portion of airflow entering an inlet to the propelling gas turbine engine through a fan assembly and a bypass ... | 11/29/2005 |
| 6966174 | Integrated bypass turbojet engines for air craft and other vehicles Turbojet engines and aircraft configurations for advantageous use of the turbojet engines; the turbojet engines utilizing ram air turbine units that centrifugally compress air isothermally for use in various combustion configurations designed for stoichiometric comb... | 11/22/2005 |
| 6964154 | Axisymmetric, throttleable non-gimballed rocket engine A rocket engine assembly is provided for a vertically launched rocket vehicle. A rocket engine housing of the assembly includes two or more combustion chambers each including an outlet end defining a sonic throat area. A propellant supply for the combustion chambers... | 11/15/2005 |
| 6948306 | Apparatus and method of using supersonic combustion heater for hypersonic materials and propulsion testing A supersonic combustion apparatus and method of using the same including a side wall cavity having an enhanced mixing system with ground-based oxygen injection for hypersonic material and engine testing. ... | 09/27/2005 |
| 6926232 | Variable cycle propulsion system with compressed air tapping for a supersonic airplane A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having at least one compressor and capable of generating thrust for supersonic flight speeds, and at least one auxiliary propulsion assembly separate from said en... | 08/09/2005 |
| 6918243 | Bi-propellant injector with flame-holding zone igniter A bi-propellant injector (66) includes a first injector element (68) and a second injector element (70) injecting a first propellant (69) and a second propellant (71), respectively, into a combustion chamber (53). A flame-ho... | 07/19/2005 |
| 6868664 | Main propulsion engine system integrated with secondary power unit A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary power unit can be mounted within an engine core compartment of the mai... | 03/22/2005 |
| 6834495 | Multi-fan system separated core engine type turbofan engine This invention provides a multi-fan system separated core engine type turbofan engine in which high pressure air is used as the working fluid for a turbine which drives a fan, thereby reducing the manufacturing costs of the turbofan engine and simplifying the consti... | 12/28/2004 |
| 6792745 | High bypass multi-fan engine A turbofan jet engine having a housing and an engine core disposed in the housing. The engine core includes at least a compressor, turbine, and a drive shaft. The drive shaft defines a drive shaft axis. A plurality of fans are disposed in the housing and each is rot... | 09/21/2004 |
| 6792746 | Separated core engine type turbofan engine A low-noise separated core engine type turbofan engine is provided in which noise generated by a control propulsion device is reduced by using high pressure air as the working fluid of a turbine for driving a control fan used in the attitude control of the airframe.... | 09/21/2004 |
| 6705569 | Axi-symmetric mixed compression inlet with variable geometry centerbody A mixed compression supersonic inlet system is provided which includes an external cowl, and an axisymmetric centerbody which preferably translates fore and aft. The centerbody of the inlet system is further provided with indexing segments which circumferentially ro... | 03/16/2004 |
| 6698693 | Solar propulsion assist This invention relates generally to method and apparatus for solar-boost assist and solar-sail assist by a mini-optics light concentrator system utilizing a dynamic ensemble of mini-mirrors. In the boost phase of a rocket ship launch, the system focusses ... | 03/02/2004 |
| 6634596 | Aircraft system architecture An integrated aircraft system which comprises an aircraft frame, a nacelle cowl mounted to the aircraft frame, a primary gas turbine engine mounted within the nacelle cowl, a secondary power system incorporated within the nacelle cowl and being driven by ... | 10/21/2003 |
| 6568171 | Rocket vehicle thrust augmentation within divergent section of nozzle Augmentation of the thrust achieved by a supersonic nozzle of continuous curvature is achieved by causing secondary combustion to occur in an annular region of the interior of the divergent section of the nozzle. The secondary combustion forms a secondary... | 05/27/2003 |
| 6488237 | Propellant cross-feed system and method A propellant cross-feed system of the present invention for use with a two-stage rocket. The rocket (or reusable launch vehicle) includes a booster and an orbiter. The booster includes a booster propellant tank that is connected to a booster engine by a b... | 12/03/2002 |
| 6415597 | Switchably coupled turbofan engines for high speed aircraft A jet engine for supersonic aircraft which enables supersonic flight and high fuel efficiency to be achieved while suppressing noise at take-off. The engine comprises a front engine consisting of a turbofan engine, and a rear engine or engines consisting ... | 07/09/2002 |
| 6378292 | MEMS microthruster array A microelectrical mechanical system (MEMS) microthruster array is disclosed. The MEMS microthruster array of the present invention can be used for maintaining inter satellite distance in small satellites. One microthruster array includes numerous microthr... | 04/30/2002 |
| 6276632 | Axi-symmetric mixed compression inlet with variable geometry centerbody A mixed compression supersonic inlet system is provided which includes an external cowl, and an axisymmetric centerbody which preferably translates fore and aft. The centerbody of the inlet system is further provided with indexing segments which circumfer... | 08/21/2001 |
