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US20130067884 |
THRUST REVERSER FOR A GAS TURBINE ENGINE
A thrust reverser includes a slider movable along an actuator shaft. An inner linkage is mounted to the slider and the inner thrust reverser door and an outer linkage is mounted to the slider and...
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US20110214409 |
Combustion Turbine in which Combustion is Intermittent
The subject of the present invention is a combustion turbine (1) for intermittent combustion with at least one combustion chamber (3) having inlet valves (2) and an ignition device (18), the at...
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US20120151897 |
SYSTEM AND METHOD FOR OPERATING A THRUST REVERSER FOR A TURBOFAN PROPULSION SYSTEM
A thrust reverser assembly for use in a turbofan engine assembly. The engine assembly includes a core gas turbine engine and a core cowl which circumscribes the core gas turbine engine. A nacelle...
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US20120174559 |
SYSTEM AND METHOD FOR CONTROLLING A GAS TURBINE ENGINE AFTERBURNER
Methods and apparatus are provided for operating a gas turbine engine. In a first operational mode, the gas turbine engine generates thrust using the propulsion turbine and not the afterburner when...
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US20120137653 |
MULTI-STAGE ROCKET, DEPLOYABLE RACEWAY HARNESS ASSEMBLY AND METHODS FOR CONTROLLING STAGES THEREOF
A deployable raceway harness assembly for use with a multi-stage rocket includes a first cable bundle configured to extend across a second stage of a multi-stage rocket from a guidance unit to a...
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US20130025256 |
Pulsed Detonation Engine
A pulsed detonation engine may include a detonation tube for receiving fuel and an oxidizer to be detonated therein, one or more fuel-oxidizer injectors for injecting the fuel and oxidizer into the...
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US20120124962 |
METHOD OF VARYING A FAN DUCT THROAT AREA
A method of varying a fan duct throat area of a gas turbine engine may include non-pivotably moving a fan nozzle outwardly relative to a longitudinal axis of the gas turbine engine during axially...
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US20120167549 |
FLADE DISCHARGE IN 2-D EXHAUST NOZZLE
An aircraft gas turbine engine has a row of FLADE fan blades disposed radially outwardly of and drivingly connected to a fan in the engine's fan section. The FLADE fan blades extend across a FLADE...
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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...
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US20130056553 |
METHOD FOR MIXING AIRFLOWS IN A TURBOFAN AND ENGINE OUTLET FOR OPERATION
The invention aims at providing a sufficient air exchange in the engine area without raising the static pressure in the outlet area of the air exchange duct. In order to do this, the invention...
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US20080092519 |
Core burning for scramjet engines
A pilot for a scramjet provides a flame front whose arrival at the wall of the scramjet combustor is delayed thereby reducing combustor heat load. By combining in-stream injection of fuel with an...
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US20120159925 |
TURBINE BASED COMBINED CYCLE ENGINE
An aircraft powerplant is disclosed that can be operated in at least three modes including as a gas turbine engine, as an engine having a ramburner, and as an engine having a forward compression...
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US20110167785 |
INTERNAL MIXING OF A PORTION OF FAN EXHAUST FLOW AND FULL CORE EXHAUST FLOW IN AIRCRAFT TURBOFAN ENGINES
An airborne mobile platform that has at least one turbofan engine assembly having a fan driven by a core engine, a short nacelle around the fan and a forward portion of the core engine, and a fan...
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US20120137655 |
VARIABLE AREA FAN NOZZLE THRUST REVERSER
A nozzle for use in a gas turbine engine includes nozzle doors coupled with a fan nacelle wherein the nozzle doors move in unison between a plurality of positions to influence a bypass airflow...
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US20110277446 |
ROCKETS, METHODS OF ROCKET CONTROL AND METHODS OF ROCKET EVALUATION UTILIZING PRESSURE COMPENSATION
Rockets, rocket motors, methods of controlling a rocket and methods of evaluating a rocket design are disclosed. In some embodiments, a method of controlling a rocket may include measuring a...
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US20110056183 |
ULTRA-EFFICIENT PROPULSOR WITH AN AUGMENTOR FAN CIRCUMSCRIBING A TURBOFAN
An ultra-efficient “green” aircraft propulsor utilizing an augmentor fan is disclosed. A balanced design is provided combining a fuel efficient and low-noise high bypass ratio augmentor fan and a l...
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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...
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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...
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US20090260343 |
SOLID PROPELLANT MANAGEMENT CONTROL SYSTEM AND METHOD
Systems and methods of controlling solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and propellant gas flow rate, rely on the position of a throttling...
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US20120011825 |
GAS TURBINE ENGINE WITH NOISE ATTENUATING VARIABLE AREA FAN NOZZLE
A bypass gas turbine engine includes a variable area fan nozzle with a leading edge region that defines an increased airfoil leading edge radius.
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US20120124963 |
METHOD OF VARYING A FAN DUCT NOZZLE THROAT AREA OF A GAS TURBINE ENGINE
A method of varying a fan duct nozzle throat area of a gas turbine engine includes pivoting a fan nozzle outwardly relative to a longitudinal axis of the gas turbine engine. The fan nozzle is...
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US20050279082 |
Hybrid rocket motor design and apparatus
This patent is for a hybrid rocket motor that allows a regeneratively cooled nozzle and combustion chamber with very limited modifications to the construction of the rocket motor made with standard...
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US20100313544 |
PROPULSION SYSTEM WITH CANTED MULTINOZZLE GRID
A propulsion system includes a canted multinozzle plate, which has a multitude of small nozzles angled (not perpendicular) to major surfaces of the multinozzle grid plate. The multinozzle plate may...
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US20080006021 |
Cooling exchanger duct
A heat exchange system for use in operating equipment in which a working fluid is utilized in providing selected operations thereof, including for use in lubricating systems for aircraft turbofan...
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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...
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US20100300065 |
CLOSED-CYCLE ROCKET ENGINE ASSEMBLIES AND METHODS OF OPERATING SUCH ROCKET ENGINE ASSEMBLIES
Closed-cycle rocket engine assemblies including a combustor assembly, a combustor jacket, a turbine, a first pump and a mixing chamber are disclosed. The combustor jacket facilitates the transfer...
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US20090288387 |
GAS TURBINE ENGINE BIFURCATION LOCATED IN A FAN VARIABLE AREA NOZZLE
A turbofan engine pylon structure having a fan variable area nozzle defined by a variable area flow system between a pylon intake and a pylon exhaust to selectively adjust a bypass flow. The...
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US20110088369 |
METHOD FOR SYNCHRONIZING THE ACTUATORS OF A MOVABLE THRUST REVERSER COWL
The invention relates to a method for controlling a plurality of actuators (9a, 9b, 9c) for a movable thrust reverser cowl (1), characterized remarkable in that the position deviation between...
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US20070283679 |
Mechanism for a vectoring exhaust nozzle
A nozzle device defines a passageway including an outlet to discharge working fluid to produce thrust. This device includes a vectoring mechanism having three or more vanes pivotally mounted across...
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US20130104521 |
GAS TURBINE ENGINE WITH TWO-SPOOL FAN AND VARIABLE VANE TURBINE
A gas turbine engine and a method of operating the gas turbine engine according to an exemplary aspect of the present disclosure includes modulating a variable high pressure turbine inlet guide...
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US20080155989 |
Operating line control of a compression system with flow recirculation
A system for controlling the operating lines of a gas turbine engine comprising a compression system which compresses an incoming flow of a gas, a bleed system which extracts gas from a bleed...
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US20080282668 |
Ether propeller
A propulsion system including an electromagnetic device for reaction with a medium; said propulsion system comprising: (e) a sectored front disc divided into an even number of charge carrying...
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US20100180570 |
Reactionless Motion (RM)
The Invention's Project of Reactionless Motion (RM) reveal a mechanically intrinsic motion technic, without motion opposites' reaction, or mass expelling. The RM invention consists in two circular...
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US20080163606 |
Variable area nozzle with woven sleeve extension
A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is attachable to a gas turbine engine for influencing flow through the fan bypass passage of the...
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US20090320442 |
DUAL MODE PROPULSION SYSTEM
A system or method of propelling a vehicle with a multimodal propulsion system is provided. This multimodal propulsion system includes a primary inlet, a high-pressure gas generator, a gas...
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US20120180451 |
Optimal Feedback Heat Energy Internal Combustion Engine And Its Applications
An internal combustion engine wherein a thermo potential heat flow in combustion is maximised by providing a feedback of an optimised amount of thermo potential heat flow that is modulated in the...
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US20120279196 |
MICROFLUIDIC FLAME BARRIER
Propellants flow through specialized mechanical hardware that is designed for effective and safe ignition and sustained combustion of the propellants. By integrating a micro-fluidic porous media...
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US20090113872 |
Electrospray source
An electrospray source useful for a variety of applications and including an emitter with a porous media flow distributor having a surface forming multiple Taylor cones. A casing about the porous...
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US20090133406 |
FAN NOZZLE OF ADJUSTABLE SECTION
Varying the flowsection for air leaving the fan as a function of flying conditions. According to the invention, the nozzle has a ring of deformable panels arranged close to its trailing edge, each...
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US20120151898 |
SYSTEM AND METHOD OF COMBUSTION FOR SUSTAINING A CONTINUOUS DETONATION WAVE WITH TRANSIENT PLASMA
An annular combustion (22) chamber and a transient plasma system (42) in communication with the annular combustion chamber (22) to sustain a spinning detonation wave. This system (42) is also...
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US20120304619 |
ENGINE FOR THRUST OR SHAFT OUTPUT AND CORRESPONDING OPERATING METHOD
An engine and a method of operating the engine are provided. The engine includes a gas turbine and fan that rotate together to provide an exhaust gas flow stream, which flows over a free turbine...
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US20080121548 |
COATING FOR COMPONENTS REQUIRING HYDROGEN PEROXIDE COMPATIBILITY
The present invention provides a heretofore-unknown use for zirconium nitride as a hydrogen peroxide compatible protective coating that was discovered to be useful to protect components that...
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US20100043395 |
PULSE DETONATION/DEFLAGRATION APPARATUS AND RELATED METHODS FOR ENHANCING DDT WAVE PRODUCTION
Pulse detonation/deflagration apparatus for providing enhanced pressure wave operating frequency and/or magnitude, and methods of increasing the frequency or the magnitude of deflagration to...
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US20110042386 |
PRESSURE VESSEL FOR PROPELLANTS, EXPLOSION PREVENTING METHOD OF THE SAME, AND MANUFACTURING METHOD OF THE SAME
A pressure vessel for propellants, an explosion preventing method of the same, and a manufacturing method of the same are disclosed. The pressure vessel for propellants comprises a body provided...
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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...
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US20100024386 |
Gas-Generator Augmented Expander Cycle Rocket Engine
An augmented expander cycle rocket engine includes first and second turbopumps for respectively pumping fuel and oxidizer. A gas-generator receives a first portion of fuel output from the first...
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US20080141656 |
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...
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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...
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US20100005777 |
DUAL FUNCTION CASCADE INTEGRATED VARIABLE AREA FAN NOZZLE AND THRUST REVERSER
A gas turbine engine system includes a nozzle having a plurality of positions for altering a discharge flow received through the nozzle from a gas turbine engine fan bypass passage. The nozzle is...
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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...
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