Matches 1 - 50 out of 86 1 2 >


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US20170058836 FEED SYSTEM AND A METHOD OF SUPPRESSING THE POGO EFFECT  
A feed system for feeding a rocket engine with a liquid propellant includes a feed circuit, and a device to vary a volume of gas in the feed circuit. The device is configured to cause a volume of...
US20130276426 Cooling Jacket with Porous Matrix  
The fluids and heat transfer theory for regenerative cooling of a rocket combustion chamber with a porous media coolant jacket is presented. This model is useful for calculating temperature...
US20170184030 SYSTEM AND METHOD FOR OPERATING A PRECOOLER IN AN AIRCRAFT  
A method for controlling a pressure control mechanism in a turbofan engine having a precooler permitting heat exchange between ambient air and bleed air includes detecting at least one of an...
US20080061559 Use of Air Internal Energy and Devices  
A method of converting air internal energy into useful kinetic energy is based on air flowing through substantially convergent nozzle, which accelerates the air as the cross section of the nozzle...
US20080010969 GAS TURBINE ENGINE AND METHOD OF OPERATING SAME  
A method for operating a gas turbine engine assembly for an aircraft that includes a wing, wherein the gas turbine engine includes a core gas turbine engine and a fan coupled to the core gas...
US20130186058 GEARED TURBOMACHINE FAN AND COMPRESSOR ROTATION  
A high-bypass ratio geared turbomachine comprises a compressor section of a high-bypass ratio geared turbomachine. The compressor section provides at least a low-pressure compressor and a...
US20130340406 FAN STAGGER ANGLE FOR GEARED GAS TURBINE ENGINE  
A gas turbine engine includes a spool, a turbine coupled with the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool and a gear assembly coupled between the...
US20150354505 PROPELLANT FEED CIRCUIT AND A COOLING METHOD  
The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit (6) for feeding a...
US20070000232 Gas turbine engine and method of operating same  
A method for operating a gas turbine engine including a core engine, a fan assembly for pressurizing air, a core stream duct, an inner bypass duct, and an outer bypass duct is provided. The method...
US20140060004 TILTROTOR VECTORED EXHAUST SYSTEM  
The exhaust system is located on each nacelle of a tiltrotor aircraft. The exhaust system includes a vector nozzle that is selectively rotatable in relation to each nacelle in order to achieve...
US20170145956 THRUST REVERSE FEATURE CONTROL  
A method for controlling a gas turbine engine includes receiving, with a controller, a thrust reverse command to activate a thrust reverse feature of the gas turbine engine. The method also...
US20100275576 SYSTEM AND METHOD FOR MANEUVERING ROCKETS  
A dual control system for a solid propellant propelled exoatmospheric kill-vehicle is disclosed. The system includes a primary solid propellant propulsion mechanism for controlling the propulsion...
US20110167784 METHOD OF OPERATING A CONVERTIBLE FAN ENGINE  
A method of operating a gas turbine engine is disclosed having the steps of directing a flow of air to a front fan stage at a selected fan flow rate, fan speed and front fan stage pressure ratio...
US20140013724 ELECTROMAGNETIC THRUSTER  
Systems and methods for electromagnetic thrusting are disclosed. An electromagnetic thrusting system includes an axially-asymmetric resonant cavity including a conductive inner surface, the...
US20100162680 GAS TURBINE ENGINE WITH EJECTOR  
The present inventions include a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet...
US20110215204 SYSTEM AND METHOD FOR GENERATING THRUST  
A thrust generator includes an air inlet configured to introduce air within the thrust generator and a plenum having a plurality of fluid injection devices. The plenum is configured to receive an...
US20160108855 DUAL MODE CHEMICAL ROCKET ENGINE, AND DUAL MODE PROPULSION SYSTEM COMPRISING THE ROCKET ENGINE  
The invention relates generally to dual mode bipropellant chemical rocket propulsion systems to be used in aerospace applications for 1) orbit raising, orbit manoeuvres and maintenance, attitude...
US20120204534 SYSTEM AND METHOD FOR DAMPING PRESSURE OSCILLATIONS WITHIN A PULSE DETONATION ENGINE  
In one embodiment, a pulse detonation engine includes a resonator configured to fluidly couple to an air flow path upstream of a pulse detonation tube. The pulse detonation engine also includes a...
US20110203253 ADVANCED FUEL COMPOSITIONS FROM RENEWABLE SOURCES, AND RELATED METHODS FOR MAKING AND USING THE FUEL  
A method for preparing a fuel composition is described, and includes the step of preparing a bio-derived fuel component that contains a mixture of iso-saturated alkanes and normal-saturated...
US20130104522 GAS TURBINE ENGINE WITH VARIABLE PITCH FIRST STAGE FAN SECTION  
A gas turbine engine with a two-spool fan and a method of operating the gas turbine engine includes modulating a pitch of a variable pitch first stage fan section of a low pressure spool, the...
US20120131901 SYSTEM AND METHOD FOR CONTROLLING A PULSE DETONATION ENGINE  
In one embodiment, a pulse detonation engine (PDE) includes a controller configured to receive signals indicative of at least one of a desired operating parameter of the PDE and a measured...
US20120124964 GAS TURBINE ENGINE WITH IMPROVED FUEL EFFICIENCY  
A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4. The low pressure turbine has...
US20120096830 TURBINE AND METHOD THEREOF  
The present disclosure relates to an improved and more efficient turbine deployed in the generation of thermal energy. The improved turbine comprises aerodynamic blades and supersonic nozzles to...
US20070180814 Direct liquid fuel injection and ignition for a pulse detonation combustor  
A system for generating thrust is provided. The system includes a first injector, an inner tube configured to receive fuel from the first injector via a first port of the inner tube, where at...
US20160208742 DiscThruster, pressure thrust based aircraft engine  
A aircraft propulsion device called DiscThrusterâ„¢ which creates thrust in the form of pressure thrust, as opposed to momentum thrust, wherein a thin round DiscThruster disc 2 spins about its disc...
US20150013303 ENGINE PROPULSION SYSTEM  
An engine propulsion system is configured to utilize bursts of media in order to create mechanical energy. The engine propulsion system includes at least one cannon, wherein each cannon is...
US20130192195 GAS TURBINE ENGINE WITH COMPRESSOR INLET GUIDE VANE POSITIONED FOR STARTING  
A gas turbine engine includes a variable inlet guide vane positioned forwardly of a low pressure compressor. The angle of the inlet guide vane is controlled at startup to increase airflow into the...
US20170037779 AIRCRAFT BOUNDARY LAYER REMOVAL WITH AUXILLIARY POWER UNIT SUCTION  
An apparatus comprising is provided including an auxiliary power unit positioned within an aircraft. A reverse thrust assembly is driven by the auxiliary power unit to provide reverse thrust...
US20140123625 ENGINE CONTROL PARAMETER TRIMMING  
A method of re-trimming an engine control parameter. Measure an engine parameter over time. Calculate change in the measured parameter per engine cycle. Determine change of thrust due to the...
US20110302906 Laser Tractor Beam  
There is provided a method of using a remote laser source to manipulate a space object having a target, comprising projecting a beam from the remote laser source, wherein the beam has a sufficient...
US20130327015 DUAL USE HYDRAZINE PROPULSION THRUSTER SYSTEM  
Some embodiments provide a dual use hydrazine propulsion thruster system. The dual use hydrazine propulsion thruster system may include a storage vessel configured to store hydrazine and a...
US20140283499 DEVICE AND A METHOD FOR FEEDING A ROCKET ENGINE PROPULSION CHAMBER  
The invention relates to a device and a method for feeding a propulsion chamber 5 of a rocket engine 1 with at least with a first propellant. The device comprises at least a first tank 2 for...
US20090293448 Simplified thrust chamber recirculating cooling system  
In some aspects a propulsion system includes a thrust chamber having a gap between an inner shell and an outer shell, the inner shell and the outer shell being attached together to form the thrust...
US20060150612 Thrust vector control  
A thrust vector control system for a flight vehicle comprises a fixed nozzle defining a first thrust vector direction and at least one exhaust deflector moveable to a location downstream of said...
US20140196436 OPERATION STABILIZATION METHOD AND OPERATION STABILIZATION APPARATUS FOR SUPERSONIC INTAKE  
An object of the present invention is to provide a technique of enlarging a stable operating range of an intake in accordance with an operating condition of an engine without using a complicated...
US20070056262 Laser propulsion thruster  
A hybrid electric-laser propulsion (HELP) thruster. A propellant has self-regenerative surface morphology. A laser ablates the propellant to create an ionized exhaust plasma that is...
US20120192543 EXHAUST NOZZLE FOR A BYPASS AIRPLANE TURBOJET HAVING A DEPLOYABLE SECONDARY COVER AND A RETRACTABLE CENTRAL BODY  
The invention relates to an exhaust nozzle for a bypass airplane turbojet comprising an annular central body, an annular primary cover surrounding the central body to define a hot stream flow...
US20130340407 CLUSTERED, FIXED CANT, THROTTLEABLE ROCKET ASSEMBLY  
A clustered, fixed cant, throttleable rocket assembly is used to propel and a steer a vessel in terrestrial or extraterrestrial applications. The fixed cant of each of at least three individual...
US20130247542 SPACE LAUNCHER PROPULSION SYSTEM IMPLEMENTING A METHOD OF REGULATING PROPELLANT COMPONENT CONSUMPTION  
A space launcher propulsion system includes: an engine fed by at least two propellant component tanks; a measurement mechanism to measure a quantity of propellant component actually consumed in...
US20130239544 Distributed pressurization system  
The present invention comprises a distributed system for providing warm, high pressure gas that is lighter weight, lower cost, and more reliable than comparable currant art pressurization systems....
US20110179766 HEAT RECOVERY SYSTEM  
An improved turbofan engine having an engine shaft and a centerbody inside of an exhaust nozzle, the turbofan engine having a fluid-filled conduit located about the centerbody and a heat recovery...
US20140109550 JET EXHAUST PISTON ENGINE  
This invention is a piston in cylinder engine using water injection into a relative vacuum heated to steam by expanding in the cylinder and by an electric arc or other heat source. The resulting...
US20130074472 INJECTOR HAVING MULTIPLE IMPINGEMENT LENGTHS  
An injector includes an injector body that has at least an injection side surface. A plurality of passages extends within the injector body for injecting combustion fluids at the injection side...
US20130061571 Laser propelled flight vehicle  
Disclosed are embodiments for producing thrust, and in particular thrust for the propulsion of a flight vehicle. The embodiments incorporate the on-board laser heating of a propellant to a plasma...
US20160281641 A PROPULSION ASSEMBLY AND A METHOD OF FEEDING PROPELLANTS  
The invention relates to the field of rocket engines, and more particularly to a propulsion assembly (10) comprising a first tank (11) for a first liquid propellant, a second tank (12) for a...
US20120198814 USE OF HOT GASES AND DEVICES  
A method of increasing internal combustion engine efficiency is based on using engine cooling air and exhaust gas by flowing this mixture into a convergent nozzle thus accelerating the gas mixture...
US20070039308 Combustion system  
A combustion system which comprises a combustion chamber (1) wherein the supply of air is intercepted and a fluid (L) formed by mixing combustibles with water is supplied, water in the fluid (L)...
US20070113535 Dual-plasma-fusion jet thrusters using DC turbo-contacting generator as its electrical power source  
New [GerTh-DawShien. V] dual-plasma flying object and [GerTh-DawShien. VI] dual-plasma-fusion flying object provide the electric start system to start their warm-up process to their steady-states,...
US20100257839 Hydrocarbon-fueled rocket engine with endothermic fuel cooling  
A rocket engine utilizes a kerosene-based fuel in a supercritical state which is catalytically converted to lighter hydrocarbons with heat from a thrust chamber assembly which operates as a heat...
US20140290211 TURBINE ENGINE INCLUDING BALANCED LOW PRESSURE STAGE COUNT  
A turbine engine includes at least a compressor section and a turbine section, each having at least a first and second portion. A ratio of turbine section second portion stages to compressor...

Matches 1 - 50 out of 86 1 2 >