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An aircraft having vertical takeoff and landing capability provided with at least first and second laterally extending paddle wheels rotatable on a central axis perpendicular to the longitudinal axis of the aircraft fuselage and between its nose and tail.
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| Number | Title | Issue Date |
| 7878003 | Fuel control system for gas turbine engine reheat apparatus A fuel control system for a gas turbine engine reheat system has a plurality of fuel metering devices for controlling fuel flow to respective ones of the reheat burners, and a plurality of throttle valves in series with the respective metering devices. One of the th... | 02/01/2011 |
| 7647776 | Fluid flow control system A fluid flow control system includes a valve, in which a control element regulates flow through a metering orifice. A further control element regulates flow through an orifice downstream of the orifice and is responsive to the pressure downstream of the orifice and ... | 01/19/2010 |
| 7437876 | Augmenter swirler pilot A turbofan gas turbine engine augmenter includes a fuel/air swirler disposed between an axially extending bypass flowpath and an axially extending exhaust flowpath. A swirler inlet is axially open to and positioned substantially normal to the bypass flowpath and a s... | 10/21/2008 |
| 7367191 | Device for fixing a burner ring in an afterburner combustion chamber of a turbojet engine Device for fixing a burner ring onto flameholder arms (14) in an afterburner combustion chamber of a turbojet engine, the burner ring being formed of ring sectors (12) placed more or less end to end and the ends of which are housed and guided between t... | 05/06/2008 |
| 7347050 | Fuel metering unit A fuel metering unit 10 for an aircraft. The unit 10 having an inlet leg 12 within which fuel flows, which leg 12 splits into controlling legs 18, 20 which rejoin downstream to form an outlet leg 30. Shut off valves 28, 3... | 03/25/2008 |
| 7305816 | Rocket augmentation for combined cycle turboaccelerator jet engine An engine for creating a propulsive force includes turbomachinery for generating a flow of hot exhaust gases and an initial thrust force, an augmentor positioned aft of the turbomachinery, and a system for injecting an oxidizer, which preferably undergoes thermal de... | 12/11/2007 |
| 7287725 | Missile control system and method A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rota... | 10/30/2007 |
| 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 |
| 7093442 | Augmentor A turbine engine augmentor has a centerbody within a gas flowpath. A flameholder is positioned in the flowpath outboard of the centerbody. A burner within the centerbody has an outlet for expelling combustion products of a first pilot fuel. A pilot fuel conduit has ... | 08/22/2006 |
| 6983601 | Method and apparatus for gas turbine engines A method for fabricating an augmentor includes fabricating an outer casing having at least one channel defined therein, fabricating a centerbody having at least one channel defined therein, fabricating a plurality of turbine frame vanes, wherein each turbine frame v... | 01/10/2006 |
| 6487847 | Gas turbine engine fuel control system A fuel control system for an aircraft gas turbine engine that includes a thrust augmentation system. An augmentor fuel pump is arranged to provide pressurized fuel to an exhaust nozzle throat area actuation system to eliminate the need for a separate hydr... | 12/03/2002 |
| 5699663 | Method of preventing instabilities produced by combustion in a turbojet engine A method of preventing instabilities due to combustion in a multi-flow turbojet engine including an afterburner into which an air-fuel mixture is injected in proportions measured in richness terms, which includes the steps of detecting experimentally, whe... | 12/23/1997 |
| 5390498 | Fuel distribution assembly A gas turbine engine fuel distribution assembly includes a fuel manifold having a fuel distribution channel therein, and a plurality of fuel distribution valves disposed inside the manifold. Each valve is disposed in the manifold for providing a bypass ch... | 02/21/1995 |
| 5335490 | Thrust augmentor heat shield A thrust augmentor heat shield for enclosing radially extending fuel pipes which can be attached to and removed from the outer duct wall from within the augmentor. The heat shield includes a hollow, elongate housing extending substantially entirely along ... | 08/09/1994 |
| 4841725 | Fuel spray device for gas turbine augmentor or afterburner The fuel spray device is adapted for use in the thrust augmentor or afterburner of a gas turbine engine. The fuel spray device includes a fuel spray manifold having a plurality of spaced apart ejection orifices and a plurality of nozzle pintles each havin... | 06/27/1989 |
| 4827714 | Gas turbine fuel control system A fuel system for a gas turbine engine in which there is provided a filter 20 having its output connected to the fuel control system 24 that controls fuel flow to the main combustors 26 of the engine. A bypass pipe 25, which has a pressure relief valve 29... | 05/09/1989 |
| 4825649 | Shutoff and pressure regulating valve Fuel is directed to the stages of an afterburner by metering flow to the stages with a single metering valve and by controlling the flow to each stage by means of an integral shutoff and regulating valve. Each shutoff valve opens and closes the fuel flow ... | 05/02/1989 |
| 4802334 | Augmentor fuel system An optical sensor (40) located in the manifold area (20) of an augmentor senses the presence of liquid. The engine control provides a high fuel flow rate from remotely located augmentor fuel control (58) until liquid is sensed. Flow is then reduced to the... | 02/07/1989 |
| 4798048 | Augmentor pilot A truncated diffuser tail cone has a step change to establish a pilot recirculation zone. Air cooled radial spray bars supply fuel to the pilot zone. Heat shields located therein are air cooled, and additional air passes through the central portion of the... | 01/17/1989 |
| 4730453 | Afterburner fuel injection system An afterburner fuel injection system is disclosed which utilizes a plurality of individual fuel injectors displayed in a radial array around the periphery of a turbojet afterburner. An atomizing chamber is associated with each fuel injection conduit to ac... | 03/15/1988 |
| 4612766 | Apparatus for compensating for variations in pressure and flow in fuel supply systems of gas turbine engines A device for compensating variations in pressure and flow in fuel supply systems of gas-turbine engines comprising a pump for supply of fuel under pressure into a fuel line and an accumulator which can be connected to the fuel line as a function of operat... | 09/23/1986 |
| 4423595 | Augmentor residual fuel drain apparatus An augmentor system for a gas turbine engine is drained of residual fuel after augmentor shutdown by means of a drain conduit connected to the augmentor fuel spray apparatus through a valve which opens upon augmentor shutdown. The outlet to the drain cond... | 01/03/1984 |
| 4370854 | Fuel valve A valve assembly for controlling the flow of a liquid fuel. The assembly includes a spring-biased movable valve member made of tungsten carbide, a captured sleeve member also made of tungsten carbide, and a readily accessible filtering screen member dispo... | 02/01/1983 |
| 4280324 | Fuel distribution device The invention concerns a fuel distribution device in a high velocity gase flow. The device consists of two coaxial, toric injection manifolds placed in close proximity with respect to each other, pierced by small diameter uniformly distributed orifices a... | 07/28/1981 |
