Did You Know...
...that the x-ray was discovered purely by accident? When German physicist Wilhelm Konrad von Roentgen was experimenting with cathode rays in 1895, he put an activated Crookes tube in a book and went out to lunch. When he returned, he discovered that a key that had also been placed in the book showed up as an image on the developed film!
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| Number | Title | Issue Date |
| 7584615 | Method of improving the ignition performance of an after-burner device for a bypass turbojet, and an after-burner device of improved ignition performance The after-burner device receives a “hot” central primary flow from the turbine of the turbojet and a “cold” peripheral secondary flow, and it has an after-burner ignition zone situated in the secondary flow that reaches the after-burner device. A fraction of... | 09/08/2009 |
| 7581398 | Purged flameholder fuel shield A fuel shield is configured for use in the afterburner of a turbofan aircraft engine. The shield includes wings obliquely joined together at a nose to conform with the leading edge region of a flameholder vane. A hood is joined to the wings and extends obliquely the... | 09/01/2009 |
| 7565804 | Flameholder fuel shield A fuel shield is configured for use in the afterburner of a turbofan aircraft engine. The shield includes wings obliquely joined together at a nose, with each of the wings including an offset mounting tab at a proximal end thereof. The wings and tabs are configured ... | 07/28/2009 |
| 7437876 | Augmenter swirler pilot A turbofan gas turbine engine augmenter includes a fuel/air swirler disposed between an axially extending bypass flowpath and an axially extending exhaust flowpath. A swirler inlet is axially open to and positioned substantially normal to the bypass flowpath and a s... | 10/21/2008 |
| 7367191 | Device for fixing a burner ring in an afterburner combustion chamber of a turbojet engine Device for fixing a burner ring onto flameholder arms (14) in an afterburner combustion chamber of a turbojet engine, the burner ring being formed of ring sectors (12) placed more or less end to end and the ends of which are housed and guided between t... | 05/06/2008 |
| 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 |
| 7287383 | Afterburner arrangement The invention relates to a burner ring for turbofan jet engines. The ring includes an upstream annular envelope which forms a channel which is open axially in the downstream direction, and a manifold for injecting fuel into the channel. The ring includes multiple se... | 10/30/2007 |
| 7231997 | Hybrid drive powered lift platform An air-based thrust recovery system for use in a powered lift platform utilizing fixed-pitch propellers is provided. The system utilizes an air compressor coupled to the drive motor of the platform and an on-board, high pressure tank for air storage. The fixed-pitch... | 06/19/2007 |
| 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 |
| 7178338 | Variable area nozzle An exhaust nozzle assembly for a gas turbine engine, the assembly comprises a main axis, an inner nozzle, an outer nozzle, a translatable centre-body and an actuator for translating the centre-body between a forward position and a rearward position. The centre-body ... | 02/20/2007 |
| 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 |
| 7137255 | Compact swirl augmented afterburners for gas turbine engines An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel and an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which th... | 11/21/2006 |
| 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 |
| 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 |
| 7013635 | Augmentor with axially displaced vane system An augmentor system minimizes acoustic pressure fluctuations on the heat release process within the augmentor by staggering the vanes therein. The alternating axial vane stagger pattern arranges the downstream set of vanes as baffles which prevent the propagation of... | 03/21/2006 |
| 6997676 | Bifurcated outlet guide vanes A turbine rear frame includes a row of outlet guide vanes extending between outer and inner bands. Each of the vanes is bifurcated into a forward prow integrally joined to an aft stern by a septum therebetween. The prow and stern collectively define the aerodynamic ... | 02/14/2006 |
| 6983601 | Method and apparatus for gas turbine engines A method for fabricating an augmentor includes fabricating an outer casing having at least one channel defined therein, fabricating a centerbody having at least one channel defined therein, fabricating a plurality of turbine frame vanes, wherein each turbine frame v... | 01/10/2006 |
| 6983586 | Two-stage pulse detonation system A two-stage pulse detonation system includes a pre-combustor and a geometric resonator connected via a converging-diverging nozzle to the pre-combustor to create a high temperature and high pressure conditions in the resonator in order to create optimal conditions f... | 01/10/2006 |
| 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 |
| 6895756 | Compact swirl augmented afterburners for gas turbine engines An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which t... | 05/24/2005 |
| 6883302 | Methods and apparatus for generating gas turbine engine thrust with a pulse detonation thrust augmenter A method enables thrust to be generated from a gas turbine engine using a pulse detonation system is provided. The engine includes an inlet portion and an exhaust portion, and the pulse detonation system includes a multi-staged pulse detonation augmentor including p... | 04/26/2005 |
| 6550235 | Combined cycle pulse detonation turbine engine operating method A turbofan engine includes a pulse detonation system to create a temperature rise and a pressure rise within the engine to generate thrust from the engine. The system includes a pulse detonation augmentor including a shock tube sub-system. The shock tube ... | 04/22/2003 |
| 5867980 | Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and an afterburner A multiple bypass turbofan engine includes a core Brayton Cycle gas generator with a fuel rich burning combustor and is provided with a variable supercharged bypass duct around the gas generator with a supercharging means in the supercharged bypass duct p... | 02/09/1999 |
| 5813221 | Augmenter with integrated fueling and cooling A turbofan engine augmenter includes an exhaust casing and a combustion liner therein which define therebetween a cooling duct for receiving bypass air. A diffusion liner adjoins the combustion liner and defines with the casing an outer inlet for receivin... | 09/29/1998 |
| 5694767 | Variable slot bypass injector system An afterburning, gas turbine aircraft engine with an annular duct for carrying bypass airflow is provided with a sliding valve type of rear Variable Area Bypass Injector (VABI) system. This rear VABI varies the direction and volume of the flow of bypass a... | 12/09/1997 |
| 5682739 | Infrared radiation suppression device A gas turbine engine of the type generating a hot gas stream and a fan stream includes a mixer having upstream and downstream portions which define first and second chutes for efficiently mixing the streams prior to discharge through an engine nozzle. Mea... | 11/04/1997 |
| 5664415 | After-burning turbo-fan engine with a fixed geometry exhaust nozzle having a variable flow coefficient An after-burning turbo-fan engine system (10) includes turbo-fan engine (14) for producing exhaust gas (20), and jet thrust therefrom. After-burning chamber (16) receives turbo-fan exhaust and injects a controllable amount of fuel into turbo-fan exhaust t... | 09/09/1997 |
| 5544480 | Augmentor light-off improvement The disclosure describes a fuel scheduling system that controls the fuel into the pilot burner of an afterburner by making fuel flow directly proportional to compressor discharge pressure at low compressor pressures, but to limit fuel flow to a fixed valu... | 08/13/1996 |
| 5483793 | Infrared radiation suppression device A gas turbine engine of the type generating a hot gas stream and a fan stream includes a mixer having upstream and downstream portions which define first and second chutes for efficiently mixing the streams prior to discharge through an engine nozzle. Mea... | 01/16/1996 |
| 5400589 | Afterburner for a turbofan engine An afterburner for a turbofan engine is disclosed having a plurality of connecting arms connecting the inner wall to the outer wall wherein each of the connecting arms defines an air chamber, an inlet communicating with the main air bypass passageway and ... | 03/28/1995 |
| 5070690 | Means and method for reducing differential pressure loading in an augmented gas turbine engine Means and method are disclosed for reducing buckling loads across an afterburner combustion liner in an augmented gas turbine engine. Means for accelerating bypass cooling airflow and then decelerating the accelerated bypass airflow for creating pressure ... | 12/10/1991 |
| 4989407 | Thrust augmentor flameholder A radial flameholder (18) extends from the augmentor case (22) through an opening (30) in a coaxial liner (20) and into the hot exhaust gas stream (26). A portion of a cool, annular fan air stream (28) enters an upstream facing opening (34) and discharged... | 02/05/1991 |
| 4989406 | Turbine engine assembly with aft mounted outlet guide vanes A turbine assembly includes an annular fairing and strut subassembly which provides mechanical strength to the turbine assembly and support for the rotor aft bearing. A readily demountable annular outlet guide vane assembly is mounted to the aft of the fa... | 02/05/1991 |
| 4899539 | Flow mixer and flame stabilizer for a turbofan engine A flow mixer and flame stabilizer structure for an afterburner of a turbofan engine is disclosed having a variable mixer to mix a portion of the cold flow with the hot flow gasses and which also forms a flame stabilizer for a secondary afterburner fuel in... | 02/13/1990 |
| 4896501 | Turbojet engine with sonic injection afterburner A propulsion system having an afterburning turbojet with turbine bypass ducts in which the afterburner fuel is added. The hot gas products and fuel mixture enters the afterburner at sonic velocity. The turbojet turbine bypass has a flow control connected ... | 01/30/1990 |
| 4893468 | Emissions control for gas turbine engine Method and apparatus for controlling the output emissions of a gas turbine engine provides an emissions combustor wherein the gas is burned locally and then thoroughly mixed with cooler unburned portions while propagating the resulting a very hot flame fr... | 01/16/1990 |
| 4833881 | Gas turbine engine augmentor A new and improved gas turbine engine augmentor including a liner having a film-coolable first portion joined to a convection-coolable second portion is disclosed. A cooling gas, such as fan bypass air, is channeled to the liner for film cooling the first... | 05/30/1989 |
| 4817378 | Gas turbine engine with augmentor and variable area bypass injector A plurality of circumferentially displaced hollow members are positioned between an outer bypass duct and the center body of the core engine. Each of the hollow members is open at the radially outward end thereof for receiving relatively cool gas from the... | 04/04/1989 |
| 4686826 | Mixed flow augmentor incorporating a fuel/air tube In a turbofan jet engine, having a circumferentially rotatable mixer segment capable of orienting the afterburner ignitors and flameholders into the path of either the exhaust gases or bypass air, a fuel-air transfer apparatus for capturing, transporting ... | 08/18/1987 |
