Did You Know...
...Chester Carlson was a patent agent who tired of having to make multiple copies of patent applications using the only duplication method available at the time: carbon paper. In 1959 he came up with a new copying system and took it to IBM for evaluation. The "experts" at IBM determined potential sales to be only 5,000 units because people wouldn't want to use a bulky machine when they had carbon paper. Carlson's invention was the xerography process, the company founded on the system is Xerox.
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| Number | Title | Issue Date |
| 8112982 | Charged particle thrust engine Several methods of increasing the thrust and energy efficiency of charged particle jet engines operating in a gaseous or liquid medium have been developed. We identify the three main components of charged particle thrust generation and provide means to take maximum ... | 02/14/2012 |
| 8112983 | Gas turbine engine A bypass turbofan gas turbine engine is started by means of electric starter motor mounted directly about a downstream end or upstream of the low pressure spool of the engine. This causes air to be driven by a fan through a bypass duct around the engine casing. Clos... | 02/14/2012 |
| 8104260 | Deswirling exhaust mixer An exhaust mixer for a gas turbine engine including a plurality of circumferentially distributed alternating inner and outer lobes, where each of the inner lobes is configured with a circumferential offset between the base and the tip thereof, and a direction of the... | 01/31/2012 |
| 8091334 | Method of operating a turbofan engine cowl assembly An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan no... | 01/10/2012 |
| 8069647 | Jet nozzle mixer An external jet nozzle mixer includes identically formed lobes. The external mixer works with the internal mixer further to mix the engine internal bypass flow with the internal jet engine core flow to level the disparate flow velocities, to reduce the peak velociti... | 12/06/2011 |
| 8015794 | Variable area flow duct employing secondary flows, and method therefor A variable area flow duct and method. In one embodiment the flow duct includes a plurality of helical vanes arranged around an interior surface wall of the flow duct. The vanes cause secondary flow vortices to be developed in the vicinity of each of the vanes that e... | 09/13/2011 |
| 8001763 | Managing spool bearing load using variable area flow nozzle A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides... | 08/23/2011 |
| 7958718 | Precision controlled variable thrust solid propellant rocket motor A multiple-stage solid rocket motor is operated in a manner designed to control its mass discharge profile. This is accomplished by providing means for igniting one stage and then igniting a subsequent stage while the first continues to burn. ... | 06/14/2011 |
| 7926259 | Turbofan engine assembly and method of assembling same A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the boos... | 04/19/2011 |
| 7921634 | Turbofan engine assembly and method of assembling same A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the boos... | 04/12/2011 |
| 7905083 | Turbofan engine assembly and method of assembling same A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the boos... | 03/15/2011 |
| 7882693 | Turbofan engine assembly and method of assembling same A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a first fan assembly disposed upstream from the core gas turbine engine, a first gearbox coupled to the first fan assembly, ... | 02/08/2011 |
| 7870720 | Inlet electromagnetic flow control A method to manipulate boundary layer conditions within a ducted fluid flow is provided. This method may be used to attach fluid flow to ducted surfaces bounding the fluid flow. This involves flowing a fluid over the surface wherein the fluid contains positively cha... | 01/18/2011 |
| 7841165 | Gas turbine engine assembly and methods of assembling same A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forwar... | 11/30/2010 |
| 7827780 | Assembly procedure for the adjustable pin-valve, fuel shut-off A protocol for assembling a fuel shut off pin valve assembly for a turbo fan engine. The protocol outlines a specific sequence of events in order to ensure failsafe incorporation of a fuel shut off valve assembly within the low pressure turbine area and specifically... | 11/09/2010 |
| 7818957 | Valve assembly for a gas turbine engine A method for channeling compressed air to a gas turbine engine augmentor is provided. The method includes coupling an annular slide valve to a gas turbine engine separation liner, coupling a valve seat to a gas turbine engine diffuser such that an airflow passage is... | 10/26/2010 |
| 7788898 | Variable coupling of turbofan engine spools via open differential gear set or simple planetary gear set for improved power extraction and engine operability, with torque coupling for added flexibility A system for transferring mechanical torque variably between a plurality of rotating machines in a turbofan engine. Two devices are used, where the first device relies upon magnetic properties of a planetary magnetic gearbox to couple the magnetic machines. The seco... | 09/07/2010 |
| 7784266 | Methods and systems for supplying air to a vehicle A method of supplying air to a vehicle is provided, wherein the method includes modulating a flow of air from between a fan assembly of a turbofan engine and a high pressure compressor of the turbofan engine with a core driven fan stage coupled in parallel to the hi... | 08/31/2010 |
| 7669404 | Localized arc filament plasma actuators for noise mitigation and mixing enhancement A device for controlling fluid flow. The device includes an arc generator coupled to electrodes. The electrodes are placed adjacent a fluid flowpath such that upon being energized by the arc generator, an arc filament plasma adjacent the electrodes is formed. In tur... | 03/02/2010 |
| 7644575 | Morphing structure A method for altering the shape of an exhaust mixing structure extending from a downstream end of a jet engine nacelle nozzle. The method may involve attaching a first end of at least one actuator to the nacelle nozzle, and attaching a second end of the actuator to ... | 01/12/2010 |
| 7640726 | Injector assembly having multiple manifolds for propellant delivery There is provided an injector assembly having two or more oxidizer manifolds and/or two or more fuel manifolds for delivery of liquid propellants to a combustion chamber such that combustion instability is reduced or eliminated during throttling. Delivery of the oxi... | 01/05/2010 |
| 7624567 | Convergent divergent nozzle with interlocking divergent flaps A nozzle system includes a multitude of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer boundary of an exhaust gas path. Each divergent flap includes longitudina... | 12/01/2009 |
| 7603842 | Method for reducing the nonsteady side loads acting on a nozzle of a rocket engine A method for reducing the nonsteady side loads acting on a nozzle of a rocket engine during a startup phase of said engine. The nozzle comprises a combustion chamber (1) where exhaust gases are generated, a divergent portion (3) in which a supersonic f... | 10/20/2009 |
| 7562520 | Method for opening a mobile cowl equipping a thrust reverser The invention concerns a method for opening a mobile cowl (2) actuated by a motor (7) and equipping a turbojet thrust reverser, characterized in that it comprises, at the start of the opening phase, a bridling step (103) whereby the speed of the... | 07/21/2009 |
| 7559191 | Ducted spinner for engine cooling A system for cooling a ducted fan aircraft engine includes a first nacelle surrounding the engine and a second nacelle substantially concentrically surrounding the first nacelle. The system includes a first spinner coupled around a base of a rotor of the ducted fan ... | 07/14/2009 |
| 7546727 | Reduced noise jet engine A system for controlling a position of jet engine exhaust mixing tabs includes a plurality of exhaust mixing tabs spaced apart from one another and extending from a lip of an exhaust nozzle of a jet engine nacelle adjacent a flow path of an exhaust flow emitted from... | 06/16/2009 |
| 7513101 | Synchronized motor thrust reverser actuation system A thrust reverser actuation system is provided that includes a synchronization system that synchronizes the actuation of at least two actuators coupled to at least two power drive units. The synchronization system includes a first synchronization shaft coupling the ... | 04/07/2009 |
| 7506498 | Pulsed detonation engines for reaction control systems Pulsed detonation engines (PDEs) are adapted for use in reaction control systems (RCS), such as thrusters for orbital correction and control (e.g., for earth-orbiting satellites), divert thrust generation and control for space-based interceptor devices, and for miss... | 03/24/2009 |
| 7478525 | System and method for controlling the temperature and infrared signature of an engine A system and method for cooling at least a portion of an engine are provided. The engine is cooled using a fuel, such as a high heat sink fuel, that is subsequently used for combustion in the engine. The fuel can be used to cool one or more of the gases and/or compo... | 01/20/2009 |
| 7472543 | Jet engine noise suppressor An embodiment of the invention is a technique to suppress noise in a jet engine. A noise suppressor includes an exhaust duct to exhaust a first stream from an air stream taken from an inlet. The exhaust duct has an exit end. The air stream is divided into the first ... | 01/06/2009 |
| 7469528 | Aircraft braking method and ducted fan jet engine for implementing the method The braking method for an aircraft propelled by at least one ducted fan jet engine, the latter comprising a fan, a jet engine core in which the primary flow circulates, a secondary flow exhaust nozzle, encased in a nacelle, comprises the step, in low-power operation... | 12/30/2008 |
| 7464535 | Rocket motor nozzle throat area control system and method A solid rocket motor including a combustion chamber, in which propellant is ignited to produce combustion gas, and a nozzle having a throat with an effective flow area, implements a system and method to inject gas into the nozzle throat to control its effective cros... | 12/16/2008 |
| 7464536 | Methods and apparatus for assembling gas turbine engines A method is provided for operating a gas turbine engine including a core engine having a core stream duct, an inner bypass duct, an outer bypass duct, and a nozzle assembly downstream of the core engine and including a core engine nozzle and a bypass nozzle separate... | 12/16/2008 |
| 7448198 | Gas turbine braking apparatus and method A device is provided which can serve one or more of the multiple functions of impeding rotation of a shaft de-coupled turbine rotor, selectively impeding rotation of a first spool of the engine, for example to permit a second spool to generate power for use in groun... | 11/11/2008 |
| 7418814 | Dual expander cycle rocket engine with an intermediate, closed-cycle heat exchanger A dual expander cycle (DEC) rocket engine with an intermediate closed-cycle heat exchanger is provided. A conventional DEC rocket engine has a closed-cycle heat exchanger terhamlly coupled thereto. The heat exchanger utilizes heat extracted from the engine's fuel ci... | 09/02/2008 |
| 7412832 | Method and apparatus for operating gas turbine engines A method for operating a gas turbine engine includes channeling compressed air from the gas turbine engine to a noise suppression system, and selectively operating the noise suppression system such that air discharged from the noise suppression system generates a pl... | 08/19/2008 |
| 7409819 | Gas turbine engine and method of assembling same A method of assembling a gas turbine engine that includes rotatably coupling a first low-pressure turbine rotor to a high-pressure turbine, rotatably coupling a second low pressure turbine rotor to the first low-pressure turbine rotor, and rotatably coupling the sec... | 08/12/2008 |
| 7395656 | Dual mode hybrid electric thruster An invention is provided for a dual mode hybrid electric thruster propulsion system. The dual mode hybrid electric thruster provides low thrust using ion/plasma exhaust only, and high thrust by mixing a neutral molecular gas with the ion/plasma exhaust. The dual mod... | 07/08/2008 |
| 7389635 | Twisted mixer with open center body An exhaust mixer assembly having a twisted mixer and an open centerbody is provided. The open centerbody is centrally disposed within the twisted mixer and helps to provide efficient cooling of exhaust air from gas turbine engines. A method for cooling exhaust air f... | 06/24/2008 |
| 7389636 | Booster rocket engine using gaseous hydrocarbon in catalytically enhanced gas generator cycle A process and a system for delivering a propellant combination to a rocket engine is described. The process comprises the steps of providing a flow of a hydrocarbon propellant fuel, raising the pressure of the hydrocarbon propellant fuel, cracking the hydrocarbon pr... | 06/24/2008 |
