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| Number | Title | Issue Date |
| 8136342 | Arrangement for controlling fluid jets injected into a fluid stream In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to... | 03/20/2012 |
| 8096105 | Turbojet engine with attenuated jet noise A plurality of hatches are distributed on the rear periphery of an engine cowl. The hatches are opened only when turbojet engine power is greater than cruising power. In an open position, the hatches draw hot air jets passing through an intermediate chamber before e... | 01/17/2012 |
| 8096104 | Fluidic vectoring for exhaust nozzle An exhaust nozzle assembly provides fluidic thrust vectoring of the primary stream to enhance aircraft maneuverability. The exhaust nozzle assembly includes a cooling air passage that supplies cooling air. A vector opening injects cooling airflow into the exhaust pa... | 01/17/2012 |
| 8087229 | Variable supersonic mach number air heater utilizing supersonic combustion A supersonic combustion apparatus including a fixed geometric nozzle having a converging area, throat, and a diverging area, at least one movable combination of a fuel injector and an oxygen injector where the combined fuel injector and the oxygen injector is locate... | 01/03/2012 |
| 8065868 | System, method, and apparatus for control input prediction and state verification of fluidic vectoring exhaust in high performance aircraft A non-invasive system, method, and apparatus for control input prediction and state verification of an aircraft's fluidic vectoring exhaust is disclosed. The control system derives a desired vector state, then predicts and sets the fluidic injection input required t... | 11/29/2011 |
| 7950218 | Bypass turbomachine with artificial variation of its throat section The invention relates to a bypass turbomachine comprising a gas turbine engine provided with a fan disposed on a longitudinal axis of the turbomachine, and an annular nacelle surrounding the engine so as to define a cold stream flow channel, the nacelle having an up... | 05/31/2011 |
| 7533517 | Exhaust nozzle for an engine of a flying craft Exhaust nozzle 14 for an engine of a flying craft, comprising a tubular body with two outlet ducts 16, 18 and boxes 26, 28 for injecting gas into the outlet ducts for the purpose of thrust vectoring, these boxes having windows 38 aligned ... | 05/19/2009 |
| 7308966 | Device for reducing jet engine exhaust noise using oscillating jets A device for reducing engine exhaust noise in an aircraft engine includes a number of oscillating jets which direct an oscillating flow into the engine exhaust. The oscillating jets are connected via channels to a turbomachinery source of high pressure gas, where th... | 12/18/2007 |
| 7309312 | Apparatus for retaining otherwise hand-held retractors and method of use A retractor retaining device retains an otherwise hand-held retractor in a retracting position within a surgical wound. The retractor retaining device includes a clamp that is attachable to a retractor support that is positioned about the wound. A retaining plate is... | 12/18/2007 |
| 7293401 | Jet engine noise suppressor An embodiment of the invention is a technique to suppress noise in a jet engine. A noise suppressor includes an exhaust duct to exhaust a first stream from an air stream taken from an inlet. The exhaust duct has an exit end. The air stream is divided into the first ... | 11/13/2007 |
| 7290738 | Dual jet emerging lift augmentation system for airfoils and hydrofoils Separate upper and lower plenums within an aircraft airfoil or a sea hydrofoil conduct fluid under different pressures to nozzle slots from which jets emerge to augment lift in accordance with different travel conditions. Lift is induced by nozzle slot emergence of ... | 11/06/2007 |
| 7234302 | Housing for a turbocharger A housing for a turbocharger forms a housing jacket (6, 7) which surrounds a rotor space (15) for receiving a turbine rotor (18). The housing jacket consists of sheet metal at least in part. A connection pipe (4′) provides for communica... | 06/26/2007 |
| 7159383 | Apparatus, method and system for gas turbine engine noise reduction An apparatus for reducing gas turbine engine noise, such as noise generated by an aircraft gas turbine engine, comprises at least one and preferably a plurality of gas injectors for injecting gas such as high pressure engine bleed air, diverted core air, air obtaine... | 01/09/2007 |
| 6996973 | Method of achieving jet separation of an un-separated flow in a divergent nozzle body of a rocket engine The invention relates to a rocket engine nozzle comprising a system for controlling jet separation of the flow in the nozzle, wherein said control system exhibits a plurality of separation triggering elements (5, 10) arranged in such a way as to generate, fro... | 02/14/2006 |
| 6983587 | Method and apparatus for thrust augmentation for rocket nozzles A method and apparatus for augmenting thrust in a rocket traveling through atmospheric gas. Rocket motor designs are provided where a throat(s) from one or more rocket motors eject high-speed primary exhaust gas in a configuration which peripherally surrounds an out... | 01/10/2006 |
| 6962044 | Method and apparatus of asymmetric injection into subsonic flow of a high aspect ratio/complex geometry nozzle The present invention reveals a method and apparatus for controlling the effective area and thrust vector angle of a fluid flow. In one embodiment, the fluid flow is controlled in an advanced, high aspect ratio, complex aperture geometry nozzle using asymmetric inje... | 11/08/2005 |
| 6951317 | Vehicle, lightweight pneumatic pilot valve and related systems therefor A vehicle, such as a missile, with a pilot valve system controls the vehicle's thrust valves despite a hostile propellant gas environment. The pilot valve system can have one or more pilot valves. Using refractory elements, the pilot valve ball reciprocates between ... | 10/04/2005 |
| 6935109 | Monoprolellant/hypergolic powered proportional actuator Systems and methods involving monopropellant and hypergolic powered proportional actuators that may be used in applications such as robotics. A blowdown tank delivers fuel to a reaction site, produce gaseous products. Those gaseous products are transported to a pres... | 08/30/2005 |
| 6758032 | System of pulsed detonation injection for fluid flow control of inlets, nozzles, and lift fans According to one embodiment of the invention, a system for altering a fluid flow includes a nozzle having a fluid flow and including a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the d... | 07/06/2004 |
| 6701705 | Gas-walled rocket nozzle The present invention comprises a rocket motor nozzle that replaces the fixed-wall throat with a "wall" created by injecting gas radially into the nozzle. By injecting gas into the flow of combustion products that are going through the nozzle, this will d... | 03/09/2004 |
| 6679048 | Apparatus and method for controlling primary fluid flow using secondary fluid flow injection A device for controlling the direction of flow of a primary fluid includes one or more injectors oriented to inject a secondary fluid against the direction of flow of the primary fluid. The injector is formed by drilling or otherwise forming a hole at an ... | 01/20/2004 |
| 6470669 | Hybrid injection thrust vector control A rocket engine (10) generates a flow of hot propulsion fluid through a nozzle (14N) for generating propulsive thrust along a thrust vector 8. Hybrid exhaust gas generators (36,38) have their exhausts (44,54) through the side of the nozzle. Each gas gener... | 10/29/2002 |
| 6354074 | Hybrid injection thrust vector control A rocket engine (10) generates a flow of hot propulsion fluid through a nozzle (14N). Hybrid exhaust gas generators (36,38) have their exhausts (44,54) through the side of the nozzle. Each gas generator includes a fuel grain (46,56) and a source of oxidiz... | 03/12/2002 |
| 6298658 | Multi-stable thrust vectoring nozzle A stream of primary gas flowing through a bi-stable thrust vectoring nozzle becomes attached to a first or second surface extending downstream of the nozzle, each surface incorporating one or more control ports for controlling to which surface the stream ... | 10/09/2001 |
| 6179251 | Thin inlet lip design for low drag and reduced nacelle size In accordance with the present invention, an aerodynamic turbo engine nacelle, disposable about an engine having an engine face, for mitigating boundary layer separation of intake airflow comprises an engine inlet. The engine inlet is provided with an int... | 01/30/2001 |
| 6125627 | Method and apparatus for spraying fuel within a gas turbine engine A fuel spraybar assembly for spraying fuel within a gas turbine engine. The spraybar assembly includes radial and lateral members that distribute fuel within the flowpath. In one embodiment two lateral members are located at the radially inward end of a r... | 10/03/2000 |
| 6112512 | Method and apparatus of pulsed injection for improved nozzle flow control An apparatus and method for varying the effective cross sectional area of an opening through a nozzle provides a controller 78 that pulses a fluidic cross flow through an injector associated with the nozzle 68 proximate to the opening of the nozzle. The c... | 09/05/2000 |
| 6112513 | Method and apparatus of asymmetric injection at the subsonic portion of a nozzle flow An apparatus and method for varying the effective cross sectional area of an opening through a fixed geometry nozzle provides a fluidic cross flow with an injector incorporated in the throat of the nozzle 68 proximate to the subsonic portion of the flow t... | 09/05/2000 |
| 6055804 | Turning vane arrangement for IR suppressors A turning vane arrangement (30) for an IR suppressor having a duct (32) adapted for receiving a primary flow PF of engine exhaust. The turning vane arrangement (30) is operative to direct a pressurized secondary flow PSF of low temperature gaseous fluid i... | 05/02/2000 |
| 5727381 | Duct flow control system A duct fixed to a vehicle propelled through an ambient fluid medium is innally provided with spaced channel passages from which the fluid medium is ejected under pressure tangentially of local duct surfaces through Coanda affected slots at the trailing e... | 03/17/1998 |
| 5706650 | Vectoring nozzle using injected high pressure air An exhaust nozzle for a gas turbine engine where pitch and yaw vectoring is achieved using fluidics by injecting high pressure air into the exhaust stream. The injected high pressure air deflects the exhaust stream, vectoring the aircraft accordingly. The... | 01/13/1998 |
| 5694766 | Method and apparatus for controlling the throat area, expansion ratio and thrust vector angle of an aircraft turbine engine exhaust nozzle using regions of locally separated flow A method and apparatus for controlling the throat area, expansion ratio and thrust vector of an aircraft turbine engine exhaust nozzle, includes means, such as deflectors and/or injected air, for producing and controlling regions of locally separated flow... | 12/09/1997 |
| 5664415 | After-burning turbo-fan engine with a fixed geometry exhaust nozzle having a variable flow coefficient An after-burning turbo-fan engine system (10) includes turbo-fan engine (14) for producing exhaust gas (20), and jet thrust therefrom. After-burning chamber (16) receives turbo-fan exhaust and injects a controllable amount of fuel into turbo-fan exhaust t... | 09/09/1997 |
| 5435489 | Engine exhaust gas deflection system Nozzles for discharging high velocity air are positioned on either side of an aircraft engine exhaust duct exit. High velocity air is discharged tangential to an outer surface of each nozzle and follows the contour thereof. The nozzles are positioned so t... | 07/25/1995 |
| 5072891 | Combination actuator and coolant supply for missile and rocket vector control The present invention relates to a strut assembly which may be selectively projected and retracted with respect to associated structure of a solid or liquid propellant rocket of missile, with such structure comprising one of, for example, a nozzle thereof... | 12/17/1991 |
| 4902254 | Propulsion device with conditioned inertia A hydraulic jet propelling apparatus has an inlet opening at one end and an outlet opening at the opposite end for a fluid passing therethrough. Between the inlet and outlet openings, a centrifugal accelerator member defines a divergent annular passageway... | 02/20/1990 |
| 4686824 | Gaseous secondary injection thrust vector control device Apparatus for modulating the thrust vector of a rocket motor by injecting t gas into the divergent section of the rocket nozzle and modulating injection of the hot gas by varying the flow from a solid propellant gas generator by controlling its flow rate ... | 08/18/1987 |
| 4424670 | Device for piloting the propulsion system of a solid propellant rocket This invention concerns the piloting of propulsion systems for solid rocket propellant missiles. It consists of a piloting assembly in which the front section of a thrust nozzle integrated in the body of a propulsion system is pierced with at least three ... | 01/10/1984 |
| 4411630 | Water-jet drive mechanism for the driving of watercraft A water-jet drive mechanism for driving of watercraft and including an elbow located in the hull of the watercraft and containing a pump or the like by which water is sucked in at the bottom of the watercraft through a suction passage and is ejected downw... | 10/25/1983 |
| 4384694 | Rocket attitude control apparatus For controlling the attitude of a rocket including a rocket fuselage and a thrust nozzle integrally attached to the rear end of the rocket fuselage and having a nozzle throat located longitudinally intermediate thereof, a rocket attitude control apparatus... | 05/24/1983 |
