Class 60/204 - Method of operation

Subclass of Class 60 - Power plants
Definition: Processes.
No. of applications: 172
Last issue date: 05/24/2012

Application No.	Application Title	Issue Date
20120124963	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 configured to move axially non-contemporaneously with the pivoting of the fan ...	05/24/2012
20120124962	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 aft translation of the fan nozzle without activating a thrust reverser....	05/24/2012
20120124964	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 an expansion ratio greater than or equal to about 5. The fan has a bypass ...	05/24/2012
20120011825	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....	01/19/2012
20110308231	SYSTEM, METHOD AND APPARATUS FOR COOLING ROCKET MOTOR COMPONENTS USING A SATURATED LIQUID VAPOR COOLANT MIXTURE A system and method of cooling a rocket motor component includes injecting a high pressure liquid coolant through an injector nozzle into a cooling chamber. The cooling chamber having a pressure lower than the high pressure liquid coolant. The liquid coolant flashes int...	12/22/2011
20110308232	Method and device to increase thrust and efficiency of jet engine A method and device for adding special substances to the gaseous outflow of the jet engine in order to create a “virtual wall” of increased pressure zone behind the jet engine nozzle which can serve as a support for the jet engine gas outflow to push against, thus i...	12/22/2011
20110302905	EYEBALL SEALS FOR GIMBALED ROCKET ENGINES, AND ASSOCIATED SYSTEMS AND METHODS Eyeball seals for a gimbaled rocket engines, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a rocket body, an engine carried by and movable relative to the rocket body, and a seal assembly. The seal assembl...	12/15/2011
20110302906	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 intensity and wavelength to cause ablation at a position on the target; i...	12/15/2011
20110277446	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 combustion chamber pressure, calculating a logarithm of the measured combustion...	11/17/2011
20110258981	MICRO-CATHODE THRUSTER AND A METHOD OF INCREASING THRUST OUTPUT FOR A MICRO-CATHODE THRUSTER A magnetically enhanced micro-cathode thruster assembly for providing long-lasting thrust is provided. The micro-cathode thruster assembly includes a tubular housing, a tubular cathode, an insulator, an anode and a magnetic field. The tubular housing includes an open di...	10/27/2011
20110219742	SUPERSONIC COMBUSTOR ROCKET NOZZLE A supersonic combustor as a component of a rocket nozzle offers improved utilization of available chemical energy that may be released from combustion gasses flowing through the rocket nozzle. A subsonic combustor sub-sonically accelerates an exothermically reacting com...	09/15/2011
20110214409	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 least one combustion chamber (3) having n...	09/08/2011
20110215204	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 exhaust gas from a gas generator and direct the exhaust gas via the plural...	09/08/2011
20110203253	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 alkanes. The method further includes the step of determining if the ratio of iso...	08/25/2011
20110179766	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 apparatus operatively connected to the fluid-filled conduit....	07/28/2011
20110167788	THRUST VECTORING APPARATUS FOR A JET ENGINE, CORRESPONDING JET ENGINE, THRUST VECTORING METHOD AND UPGRADING METHOD FOR A JET ENGINE The thrust vectoring apparatus comprises: a housing defining a primary outlet for emitting the primary jet; Coanda surfaces extending from opposing regions of said housing, and radially spaced from the primary outlet such that a step is defined between each Coanda surfa...	07/14/2011
20110167787	PULSE JET ENGINE The present invention relates to pulse jet engines. More specifically, the present invention concerns a pulse jet engine which uses fluidic valving rather than unreliable mechanical valves, incorporates two combustion chambers with approximately the same but approximate...	07/14/2011
20110167785	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 exhaust duct through the nacelle. A mixer duct shell is disposed substanti...	07/14/2011
20110167784	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 corresponding to a selected first operating power level, pressurizing a por...	07/14/2011
20110167786	INTERNAL MIXING OF A PORTION OF FAN EXHAUST FLOW AND FULL CORE EXHAUST FLOW IN AIRCRAFT TURBOFAN ENGINES An integrated, single piece mixer-center body ventilation apparatus is disclosed for use with a turbofan jet engine. The apparatus may incorporate a circumferential forward body portion adapted to be coupled to an aft end of a core engine turbine case of the jet engine,...	07/14/2011
20110154804	EXHAUST FOR A GAS TURBINE ENGINE A gas turbine engine is provided having an offtake passage that in one form is capable of extracting a bypass flow from the engine. The airflow traversing the offtake passage is introduced to an exhaust flow of the gas turbine engine through an offtake outlet. The offta...	06/30/2011
20110088369	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 adjacent actuators is measure...	04/21/2011
20110088368	THERMALLY-INTEGRATED FLUID STORAGE AND PRESSURIZATION SYSTEM A propulsion system may be operated by determining pressure in a cryogenic liquid tank storing a fluid and cooling the cryogenic liquid tank in response to determining that the pressure is greater than a predetermined value. The cryogenic liquid tank may be pressurized ...	04/21/2011
20110056183	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 low-noise shrouded high bypass ratio turbofan. Three mass flow streams...	03/10/2011
20110048025	NOZZLE PLASMA FLOW CONTROL UTILIZING DIELECTRIC BARRIER DISCHARGE PLASMA ACTUATORS Dielectric barrier discharge plasma actuators are used to manipulate exhaust flow within and behind a jet engine nozzle. The dielectric barrier discharge plasma actuators may be used to direct cooling airflow near the surface of the nozzle to reduce heating of the nozzl...	03/03/2011
20110042386	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 with a cylindrical portion between a forward dome and an aft dome, and has ...	02/24/2011
20110036067	AIRFLOW MODULATION FOR DUAL MODE COMBINED CYCLE PROPULSION SYSTEMS The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combust...	02/17/2011
20110005192	COOLING SYSTEM FOR AN AIRCRAFT, AIRCRAFT COMPRISING THE COOLING SYSTEM AND COOLING METHOD A cooling system for an aircraft includes a cooling circuit for transporting a coolant, with the cooling circuit running to a component in the aircraft that is heated up during flying in order to take up heat from the heated-up component via the coolant. The cooling cir...	01/13/2011
20100313545	GAS TURBINE ENGINE NOZZLE CONFIGURATIONS In one embodiment, a gas turbine engine exhaust nozzle comprises a housing having a length which extends along a central longitudinal axis and comprising an interior surface and an exterior surface, and a row of chevrons extending from an aft end of the housing, the che...	12/16/2010
20100313544	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 be a cylindrical section or plate, and the multitude of nozzles may be s...	12/16/2010
20100300065	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 of heat from the combustor assembly into a fluid and the turbine is driven...	12/02/2010
20100275575	METHOD AND SYSTEMS FOR CONTROLLING ENGINE THRUST USING VARIABLE TRIM A method and systems for controlling a thrust output of a gas turbine engine are provided. The system includes a first sensor for measuring a first engine operating parameter, a second sensor for measuring a first engine condition parameter, and a processor programmed t...	11/04/2010
20100275576	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 of the kill-vehicle during a first phase of rocket flight, and a secondary...	11/04/2010
20100269486	GAS TURBINE ENGINE HAVING SLIM-LINE NACELLE A method of providing a slim-line nacelle for a gas turbine engine includes the steps of detecting a windmilling condition and increasing a discharge airflow area of a variable area fan nozzle in response to the detection of the windmilling condition....	10/28/2010
20100269484	SOLID PROPELLANT GAS CONTROL SYSTEM AND METHOD Systems and methods of controlling solid propellant gas pressure and vehicle thrust are provided. Propellant gas pressure and a vehicle inertial characteristic are sensed. Propellant gas pressure commands and vehicle thrust commands are generated. A propellant gas press...	10/28/2010
20100269485	INTEGRATED VARIABLE AREA NOZZLE AND THRUST REVERSING MECHANISM A variable area fan nozzle for use with a gas turbine engine system includes a nozzle having a cross-sectional area associated with a discharge air flow from a fan bypass passage. The nozzle is selectively moveable between multiple static positions for varying the cross...	10/28/2010
20100257839	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 exchanger. This process is facilitated by a fuel stabilization deoxygenator...	10/14/2010
20100242433	METHOD FOR IMPROVING THE PERFORMANCE OF A BYPASS TURBOJET ENGINE Method for improving the performance of a bypass turbojet engine. According to the invention, the area of the annular outlet orifice (6) for the cold stream (9) is tailored to suit a reference value of the expansion ratio of said cold stream (9) whi...	09/30/2010
20100236216	TURBOFAN ENGINE WITH VARIABLE AREA FAN NOZZLE AND LOW SPOOL GENERATOR FOR EMERGENCY POWER GENERATION AND METHOD FOR PROVIDING EMERGENCY POWER A turbofan engine (10) employs a flow control device (41) that changes an effective exit nozzle area (40) associated with a bypass flow path (B) of the turbofan engine. A spool (14) couples a fan (20) to a generator (52). The tu...	09/23/2010
20100223903	VARIABLE PRESSURE RATIO COMPRESSOR A compressor of a gas turbine engine may have a bypass that routes a compressed air flow from within the compressor and directs the compressed air flow to a combustor. The bypass may have an inlet positioned just ahead of a downstream stage of the compressor and an outl...	09/09/2010

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Class 60/204 - Method of operation