Did You Know...
...that the video game, Pong, was invented by a guy who graduated at the bottom of his engineering class? Nolan Bushnell spent more time running the games at a local amusement park than he did on his studies at the University of Utah. His dreams of working for Disney's amusement empire were dashed when the company wouldn't hire him. Taking a boring job, Nolan daydreamed about electronic versions of popular games. He invented Pong, the first video game, and went on to found Atari Co.
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| Number | Title | Issue Date |
| 8127531 | Radially translating fan nozzle nacelle A variable area nozzle system for a turbofan gas turbine engine comprises a fan duct inner wall, a fan duct outer wall and a fan nozzle. The fan duct outer wall is disposed in radially-spaced relation to the fan duct inner wall. The fan nozzle defines at least a por... | 03/06/2012 |
| 8127532 | Pivoting fan nozzle nacelle A variable area nozzle system for a gas turbine engine includes a fan duct inner wall, a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, and a fan nozzle. The fan nozzle defines at least a portion of the fan duct outer wall and i... | 03/06/2012 |
| 8074440 | Gas turbine engine with axial movable fan variable area nozzle A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides aftward relative to the fixed fir... | 12/13/2011 |
| 7726116 | Turbofan engine nozzle assembly and method of operating same A nozzle assembly for a gas turbine aircraft engine is provided. The nozzle assembly includes a nacelle and a core cowl positioned at least partially within the nacelle such that the core cowl and the nacelle are aligned substantially concentrically to each other de... | 06/01/2010 |
| 7614210 | Double bypass turbofan A variable cycle turbofan engine includes first and second fans independently joined to respective turbines. A first bypass duct surrounds a core engine disposed in flow communication with the second fan. A second bypass duct surrounds the first bypass duct in flow ... | 11/10/2009 |
| 7475532 | 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... | 01/13/2009 |
| 7416051 | Assembly and method for fan noise reduction from turbofan engines using dynamically adaptive Herschel-Quincke tubes An assembly useful in reducing aircraft engine noise such as turbofan engine noise (730) comprises: (1) at least one tube “H-Q” having an inlet end (738), an outlet end (740) and a central tube portion therebetween; an (ii) at least one actu... | 08/26/2008 |
| 7395657 | Flade gas turbine engine with fixed geometry inlet An aircraft propulsion system includes a gas turbine engine having a fan section, at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to the fan section, the row of FLADE fan blades radially extending across a FLADE duct circu... | 07/08/2008 |
| 7353647 | Methods and apparatus for assembling gas turbine engines A method facilitates assembling a gas turbine engine including a compressor and a rotor assembly coupled in axial flow communication downstream from the compressor. The method comprises coupling a bypass system in flow communication with the compressor to channel a ... | 04/08/2008 |
| 7334409 | Retractable afterburner for jet engine The present invention is a retractable afterburner shroud for use upon a jet engine. The retractable shroud conforms to an outer surface of a jet engine. The afterburner shroud is affixed by a plurality of moveable support arms. The afterburner shroud is retractable... | 02/26/2008 |
| 7299635 | Device for mixing two flows of fluid which are initially guided separate from one another in a bypass jet engine The invention relates to a device for mixing two fluid flows, initially guided separately from one another, in a two-circuit reaction engine, a mixing tube which encloses a hot core stream being provided, along the outer shaped lateral surface of which a cold bypass... | 11/27/2007 |
| 7246484 | FLADE gas turbine engine with counter-rotatable fans An exemplary embodiment of a FLADE counter-rotating fan aircraft gas turbine engine includes at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to one of axially spaced-apart first and second counter-rotatable fans. A core en... | 07/24/2007 |
| 7232287 | Controlling a plurality of devices Four actuators are instructed to move to a condition indicated by a demand line 81. Their actual conditions are indicated by four arrows. The method determines if the range 84 of actual conditions exceeds a threshold value, representing an unacceptable... | 06/19/2007 |
| 7231770 | Onboard supplemental power system at varying high altitudes Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a super... | 06/19/2007 |
| 7219490 | Nested core gas turbine engine A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section. ... | 05/22/2007 |
| 7216831 | Shape changing structure In one preferred embodiment, a structure is provided that includes a body having a first wall and a second wall. At least one appending component extends from an end of the body and includes a first skin and second skin. The structure additionally includes at least ... | 05/15/2007 |
| 7188467 | Methods and apparatus for assembling a gas turbine engine A method for assembling a gas turbine engine includes providing a core engine, and providing a flade system including a flade stream augmentor positioned within a flade duct. The method also includes channeling airflow through the core engine to produce engine thrus... | 03/13/2007 |
| 7185484 | Methods and apparatus for assembling a gas turbine engine Methods and apparatus for assembling a gas turbine engine are provided. The method includes coupling a first turbine shaft that includes m rows of turbine blades within the gas turbine such that the first turbine shaft is rotatable in a first direction, and coupling... | 03/06/2007 |
| 7174718 | Device for controlling propulsive jet mixing for aircraft jet engines A device for controlling propulsive gas mixing at an outlet of an aircraft jet engine, wherein propulsive jets are composed of a hot primary jet exiting from a nozzle of the jet engine and a secondary flux flowing between an external wall of the nozzle and an intern... | 02/13/2007 |
| 7174704 | Split shroud exhaust nozzle A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased diameter. An inner shroud surrounds the centerbody and cooperates with t... | 02/13/2007 |
| 7147183 | Lift system for an aerial crane and propulsion system for a vehicle The present invention provides an improved lift system for an aerial crane incorporating a wing, coanda and curved surface. The arrangement of the wing, coanda and curved surface use and induce airflow to create additional lift through an increase in airflow mass, d... | 12/12/2006 |
| 7140174 | Methods and apparatus for assembling a gas turbine engine A method for assembling a gas turbine engine includes providing a core engine, an inner fan assembly, and a fladed fan assembly, coupling a plurality of airflow ducts to the engine including an inner fan duct for channeling airflow through the inner fan assembly, a ... | 11/28/2006 |
| 7114323 | Jet exhaust noise reduction system and method A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft en... | 10/03/2006 |
| 7111462 | Onboard supplemental power system at varying high altitudes Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a super... | 09/26/2006 |
| 7108569 | Axial flow pump or marine propulsion device A multistage axial-flow pumping or marine propulsion device having fixed or variable pitch stators between rotors. Stator vanes are designed to lower internal fluid speed without sacrificing total pressure as working fluid travels toward the discharge nozzle. A vari... | 09/19/2006 |
| 7100358 | Turbine exhaust case and method of making A structural turbine exhaust case of a gas turbine engine, comprises inner and outer case portions; a bearing housing connected to the inner case portion for supporting a main spool of the gas turbine engine; and a plurality of airfoils extending between the inner a... | 09/05/2006 |
| 7093442 | Augmentor A turbine engine augmentor has a centerbody within a gas flowpath. A flameholder is positioned in the flowpath outboard of the centerbody. A burner within the centerbody has an outlet for expelling combustion products of a first pilot fuel. A pilot fuel conduit has ... | 08/22/2006 |
| 7093793 | Variable cam exhaust nozzle An exhaust nozzle includes an exhaust duct with an outlet and a row of radial apertures upstream therefrom. A radial frame surrounds the duct upstream from the apertures. A row of flaps are hinged to the frame to selectively cover and uncover the apertures for contr... | 08/22/2006 |
| 7089744 | Onboard supplemental power system at varying high altitudes Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a super... | 08/15/2006 |
| 7077623 | Fluid flow machine with integrated fluid circulation system A fluid-flow machine includes at least one rotor and a free number of stators flown by a fluid, with at least one blade thereof positioned on throat-confining surfaces provided with both a device for fluid removal from the flow path and a device for fluid supply int... | 07/18/2006 |
| 7062901 | Variable geometry nozzle with flexible side wall The disclosed device is directed toward a periodic combustion propulsion system. The periodic combustion propulsion system comprises at least one periodic combustion chamber configured to contain periodic combustion and at least one supersonic exhaust nozzle coupled... | 06/20/2006 |
| 7055329 | Method and apparatus for noise attenuation for gas turbine engines using at least one synthetic jet actuator for injecting air A method enables a gas turbine engine to be operated. The method comprises channeling exhaust gases from a core engine through an exhaust assembly and past at least one flow boundary surface, and selectively operating a noise suppression system extending from the at... | 06/06/2006 |
| 7055648 | Assembly and method for fan noise reduction from turbofan engines using dynamically adaptive Herschel-Quincke tubes An assembly useful in reducing aircraft engine noise such as turbofan engine noise (730) comprises: (i) at least one tube “H-Q” having an inlet end (738), an outlet end (740) and a central tube portion therebetween; and (ii) at least one act... | 06/06/2006 |
| 7010905 | Ventilated confluent exhaust nozzle An exhaust nozzle includes an outer duct surrounding an inner duct. The inner duct includes a main outlet, and a row of apertures spaced upstream therefrom. The outer duct includes a row of intakes at a forward end, an auxiliary outlet at an aft end, and surrounds t... | 03/14/2006 |
| 7000378 | Gas turbine engine exhaust nozzle having a noise attenuation device driven by shape memory material actuators A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which extend in a generally axial direction from a downstream portion of the n... | 02/21/2006 |
| 6976361 | Ventilation channels in an afterburner chamber confluence sheet The invention relates to ventilating the confluence sheet of an afterburner chamber of an aviation turbomachine, including, upstream from the afterburner chamber: a diffuser defined by a confluence sheet disposed inside a casing, said casing and said confluence shee... | 12/20/2005 |
| 6968701 | Engine integrated auxiliary power unit The present invention relates to an engine integrated auxiliary power unit. The engine comprises a high pressure spool which includes a high pressure compressor connected to a high pressure turbine and a low pressure spool which includes a low pressure compressor co... | 11/29/2005 |
| 6966189 | System for sealing the secondary flow at the inlet to a nozzle of a turbomachine having a post-combustion chamber A turbomachine comprising, downstream from the turbine, a post-combustion chamber defined by a thermal protection lining inside a casing defining an annular channel for a secondary flow, an annular diaphragm secured at the downstream end of said channel, said nozzle... | 11/22/2005 |
| 6966175 | Rotary adjustable exhaust nozzle An exhaust nozzle includes an exhaust duct with an outlet and a row of radial apertures upstream therefrom. A radial frame surrounds the duct upstream from the apertures. A row of flaps are hinged to the frame to selectively cover and uncover the apertures for contr... | 11/22/2005 |
| 6945031 | Recessed engine nacelle A gas turbine engine nacelle includes an inner skin surrounded by a radially outer skin. The inner skin terminates at an exhaust outlet. The outer skin terminates at a recess in the inner skin extending into a closed cavity under the outer skin. ... | 09/20/2005 |
