Bizarre Patents
A banana protective device for storing and transporting a banana carefully.
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 7770381 | Duct burning mixed flow turbofan and method of operation A gas turbine engine includes a turbomachinery core operable to generating a first flow of pressurized combustion gases, the core having an exit plane; a fan disposed upstream of the core adapted to extract energy from the core and generate a first flow of pressuriz... | 08/10/2010 |
| 7299635 | Device for mixing two flows of fluid which are initially guided separate from one another in a bypass jet engine The invention relates to a device for mixing two fluid flows, initially guided separately from one another, in a two-circuit reaction engine, a mixing tube which encloses a hot core stream being provided, along the outer shaped lateral surface of which a cold bypass... | 11/27/2007 |
| 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 |
| 7264203 | Spider actuated thrust reverser A thrust reverser includes reverser doors circumferentially spaced around a nacelle. An arcuate yoke is disposed coaxially around the nacelle. An actuator is mounted tangentially to the yoke for rotary movement thereof. Actuator rods join the doors to the yoke for s... | 09/04/2007 |
| RE39796 | Method of eliminating mach waves from supersonic jets A method and device for reducing the amount of noise generated by a supersonic jet engine is provided. The method creates an envelope of air around the supersonic jet exhaust. The temperature and velocity of this envelope is controlled to eliminate or reduce the for... | 08/28/2007 |
| 7216475 | Aft FLADE engine An aft FLADE gas turbine engine includes a fan section drivenly connected to a low pressure turbine section, a core engine located between the fan section and the low pressure turbine section, a fan bypass duct circumscribing the core engine and in fluid communicati... | 05/15/2007 |
| 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 |
| 7163177 | Airship ballast system An airship ballast system includes an engine driven propeller and a cooling tube that is positioned coplanar with the propeller and outside its tip path. One end of the cooling tube is connected to receive exhaust gases from the engine while the other end is connect... | 01/16/2007 |
| 7117797 | Pyrotechnic charge structure A pyrotechnic charge structure, in particular for use as propellant in a rocket motor, is disclosed. The charge structure has a predetermined longitudinal extension and cross sectional area adapted to the intended purpose. The pyrotechnic charge structure (1; 2; ... | 10/10/2006 |
| 7051659 | Projectile structure A scramjet has a cowl, a center structure, and a plurality of wide pylons connecting the cowl to the center structure, with scramjet engines positioned between adjacent pylons. Leading surfaces of adjacent pylons converge to one another to provide side wall compress... | 05/30/2006 |
| 6935098 | Turbomachine nozzle with noise reduction A nozzle comprising an inner barrel, a centerbody disposed inside the inner barrel so as to define a first channel for a primary flow, and an outer barrel surrounding the inner barrel so as to define a second annular channel for a secondary flow, the free end of the... | 08/30/2005 |
| 6845606 | Variable cycle propulsion system with gas tapping for a supersonic airplane, and a method of operation A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having means for producing exhaust gas and a gas exhaust nozzle for generating thrust for supersonic flight speeds, and at least one separate auxiliary propulsion... | 01/25/2005 |
| 6845607 | Variable area plug nozzle A center plug is configured for variable area use in an exhaust nozzle. A forward portion of the plug includes an inlet having a closing flap therein, and an aft portion of the plug includes an outlet. The flap is selectively open during aircraft takeoff operation a... | 01/25/2005 |
| 6837456 | Microjet based control system A microjet based control system helps control the feedback loop that is created by an impinging jet of a STOVL aircraft. A plurality of microjets circumferentially encompass the outer periphery of the impinging jet and each issues a jet flow toward the jet flow crea... | 01/04/2005 |
| 6792747 | Turbo shaft engine with acoustical compression flow amplifying ramjet A turbo shaft engine for amplifying an air stream flow rate includes a turbine fan assembly and gas generator. The gas generator includes a primary air duct defining intake and outlet ports. A combustion chamber is connected to the primary air duct for igniting an a... | 09/21/2004 |
| 6766638 | Hydrogen peroxide based propulsion system A micro air vehicle is propelled by a bipropellant micro engine supplied with hydrogen peroxide and a hydrocarbon fuel. The hydrogen peroxide is decomposed to produce steam and oxygen at high temperature and the hydrocarbon fuel is burnt within a combustion chamber ... | 07/27/2004 |
| 6763653 | Counter rotating fan aircraft gas turbine engine with aft booster A gas turbine engine turbine assembly includes a high pressure spool having a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft which is rotatable about an engine centerline. A low pressure turbine has counter rotatable... | 07/20/2004 |
| 6647709 | Turbo shaft engine with acoustical compression flow amplifying ramjet A turbo shaft engine for amplifying an air stream flow rate includes a plurality of blades positioned within a turbine housing for rotation by an intake air flow. A gas generator having a primary air duct defines intake and outlet ports, the intake port r... | 11/18/2003 |
| 6591602 | Ejection seat rocket motors A rocket motor is disclosed that is suitable for use with an ejection seat. The rocket motor includes a combustion chamber, and has a plurality of spaced apart outlets arranged in fluid communication with the combustion chamber, to allow the passage of ex... | 07/15/2003 |
| 6508055 | Variable mode jet engine--suitable for STOVL This jet engine comprises a complete low bypass turbofan unit 1 including secondary fan unit 2 and engine core, ahead of which sits a larger diameter main fan unit 3 driven from the front of the secondary fan via a long drive shaft 4. A center portion of ... | 01/21/2003 |
| 6079202 | Reloadable/modular solid propellant rocket motor A modular rocket motor having a cylindrical housing with one end having an inwardly curved rim and the other end having internal threads. A heat-resistant plastic liner and a threaded nozzle cap are slidingly insertable with the cylindrical housing, with ... | 06/27/2000 |
| 5916127 | Method of eliminating Mach waves from supersonic jets A method and device for reducing the amount of noise generated by a supersonic jet engine is provided. The method creates an envelope of air around the supersonic jet exhaust. The temperature and velocity of this envelope is controlled to eliminate or red... | 06/29/1999 |
| 5343698 | Hexagonal cluster nozzle for a rocket engine A rocket engine thrust nozzle assembly is disclosed wherein combustion products from a plurality of rocket engines having hexagonally-shaped exhaust areas flow to the inlet of a main nozzle that transitions the flow of the combustion products from a non-c... | 09/06/1994 |
| 5311735 | Ramjet bypass duct and preburner configuration A combined turbofan and ramjet aircraft engine includes a forward bypass duct which allows the engine to operate more efficiently during the turbofan mode of operation. By mounting a ramjet preburner in the forward duct and isolating this duct from the tu... | 05/17/1994 |
| 5305600 | Propulsion engine The rotor of a fan disposed in the annular noncombusted air flow duct of a urbojet propulsion engine of the bypass type is carried by a rotary body which includes the rotor assembly of a multi-stage turbine driven by noncombusted air supplied thereto by an... | 04/26/1994 |
| 5284014 | Turbojet-ramjet hypersonic aircraft engine A combination turbojet-ramjet engine for powering a hypersonic aircraft is disclosed wherein the intake duct for the ramjet portion of the engine is centrally located within the turbojet portion of the engine in order to improve the access from outside th... | 02/08/1994 |
| 5131223 | Integrated booster and sustainer engine for a missile The weight of a start cartridge in a cruise missile (10) of the type having a booster rocket (60) for initiating flight and a thrust producing gas turbine (12) for sustaining flight may be eliminated by placing the gas outlet (62) for the rocket engine (6... | 07/21/1992 |
| 5067316 | Rocket engine expansion nozzle with complementary annular nozzle The invention comprises an expansion nozzle for a rocket engine destined to function successively in atmospheric and space conditions. The nozzle is comprised of a main wall defining a surface of revolution that splays outwardly and further comprises a co... | 11/26/1991 |
| 5038560 | Fluid outlet duct A cooling air outlet duct for a heat exchanger of a gas turbine engine is provided with a rotatable wall portion. The rotatable wall portion is rotatable about a pivot positioned at its upstream end so that the total flow area between the downstream end o... | 08/13/1991 |
| 5010730 | Gas-fed hybrid propulsion system Self-contained hybrid propulsion systems have long been recognized as a class of propulsion systems that combine a liquid propellant and a solid propellant into a single system. The propellants are stored separately and the liquid propellant is delivered ... | 04/30/1991 |
| 4996839 | Turbocharged compound cycle ducted fan engine system A turbocharged, compounded cycle ducted fan engine system includes a conventional internal combustion engine drivingly connected to a fan enclosed in a duct. The fan provides propulsive thrust by accelerating air through the duct and out an exhaust nozzle... | 03/05/1991 |
| 4964340 | Overlapping stage burn for multistage launch vehicles The invention relates to a multistage launch vehicle and method of multistage launch vehicle operation in which at least one subsequent motor stage is ignited following lift-off in partially overlapping relationship with its immediately preceding motor st... | 10/23/1990 |
| 4938021 | Sustainer propulsion system The high cost of fabrication of a turbojet propulsion system 12 for a missile having an engine 18, mounted within a casing 14, including an inlet 20 to a compressor 22 and an exhaust gas outlet 24 is avoided in a structure having a propulsion system 12 wi... | 07/03/1990 |
| 4919364 | Propulsion system for hypersonic flight A propulsion system for an aircraft capable of hypersonic flight combines a turbo-jet with a ramjet which are so arranged that the ramjet or jets are located directly adjacent to the aircraft body while the turbo-jet or jets are located away from the airc... | 04/24/1990 |
| 4866930 | Membrane seal for application to pulsed rocket motors A thin membrane of high strength but ductile material is placed over a perforated structural support, thus allowing high pressure on the membrane side of the support to separate one chamber from another. Upon application of pressure through the perforated... | 09/19/1989 |
| 4815282 | Turbocharged compund cycle ducted fan engine system A turbocharged, compounded cycle ducted fan engine system includes a conventional internal combustion engine drivingly connected to a fan enclosed in a duct. The fan provides propulsive thrust by accelerating air through the duct and out an exhaust nozzle... | 03/28/1989 |
| 4803837 | Dual cycle gas turbine engines A gas turbine includes a change-over valve having a rotatable part and a static part. The valve is disposed between upstream and downstream compressors of the engine for selectively directing flows from the upstream compressor and an auxiliary inlet to th... | 02/14/1989 |
| 4791782 | Fluid outlet duct The invention relates to fluid outlet ducts particularly cooling air outlet ducts of a gas turbine engine. A fluid outlet duct for a gas turbine engine is divided across its width into a plurality of second plenum chambers, each of the second plenum chamb... | 12/20/1988 |
| 4713935 | Vectorable nozzles for aircraft One major problem associated with the design of high-speed vertical take-off or landing aircraft is the requirement to have the front vectorable nozzles of the aircraft deployed in the airstream which passes over the fuselage of the aircraft when they are... | 12/22/1987 |
| 4587803 | Valve for diverting fluid flows in turbomachines A valve for selectively changing the direction of flow of working fluid through a variable cycle engine which comprises a first and second compressor 14,16 spaced along a flow duct 26. The duct 26 having air intakes 42 leading to the second compressor 16 ... | 05/13/1986 |
