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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...
US20130219854 AIR-COOLED OIL COOLER FOR TURBOFAN ENGINE  
A turbofan gas turbine engine comprises a nacelle cowl and a core engine. A bypass duct is between an outer surface of a casing of the core engine, and an inner surface of the nacelle cowl. An air...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
US20140007554 ROCKET MOTOR WITH MEANS FOR USER ADJUSTABLE THRUST  
A rocket having a motor with a user adjustable thrust is provided. The rocket includes a main cylinder containing a rocket propellant, the propellant configured to generate gas during operation and...
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...
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...
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...
US20130199154 RAMJET SUPERHEATER  
The present invention provides a regenerative superheater system for an ejector ramjet engine. The invention includes a superheater in thermal communication with the combustion chamber of the...
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...
US20140223884 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...
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...
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...
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...
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...
US20140007555 TURBINE GENERATOR ASSEMBLY FOR THRUST VECTOR CONTROL  
A system and method includes a thrust system; a generator for providing electric power to at least one electromechanical actuator of the thrust system; a turbine for driving the generator; a speed...
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.
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...
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...
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...
US20130199153 METHOD AND APPARATUS TO CONTROL PART-LOAD PERFORMANCE OF A TURBINE  
A method of controlling the part-load performance of a turbine includes generating a bypass flow in the turbine by removing a portion of a compressed fluid from a compressor of the turbine,...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
Matches 1 - 50 out of 191 1 2 3 4 >