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Match Document Document Title
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...
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...
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...
7506513 Device for feeding air and fuel to a burner ring in an after-burner chamber  
A device for feeding air and fuel to a burner ring in an after-burner chamber, including a plurality of flame-holder arms extending radially about the axis of the chamber from an outer casing, and...
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...
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...
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...
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...
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...
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...
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,...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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...
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....
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...
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...
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...
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,...
4490973 Flameholder with integrated air mixer  
A flameholder in an afterburner incorporates an improved mixer which includes a small duct for capturing a small percent of hot gas stream flow and routing the same outwardly along the gutter of...
4461146 Mixed flow swirl augmentor for turbofan engine  
An augmentor in a turbofan jet engine utilizes a crossover chute assembly direct portions of the bypass fan stream inwardly and portions of the hot core stream outwardly into alternating radial...
4418531 Flameholder stabilization plate for an aircraft engine afterburner system  
A flameholder stabilization plate attaches to the lower part of a flameholding baffle disposed in an afterburner system of a turbofan engine. The plate includes extension tabs which extend...
4335573 Gas turbine engine mixer  
An afterburning turbofan engine includes amixer for mixing the engine generated hot gas and fan streams prior to discharge through the engine nozzle. The mixer includes a fixed upstream portion and...
4305248 Hot spike mixer  
A mixer at the exit opening of a high performance jet engine to prevent premature migration of the core flow into the duct stream thereby operating to eliminate hot streaks in the augmentor and...
4285194 Apparatus and method for controlling fan duct flow in a gas turbine engine  
A fan duct flow control method and apparatus is provided for controlling fan bypass airflow at an inlet into an exhaust duct cooling annulus of a variable cycle gas turbine engine. The flow control...
4203285 Partial swirl augmentor for a turbofan engine  
A partial swirl augmentor for a turbofan engine having an annular duct for directing hot gases into the augmentor combustion chamber. Located within the combustion chamber is a piloted vee-gutter...
4185461 Turbojet engine with combustor bypass  
A propulsion system having an afterburning turbojet with the fuel supplied at the inlet to the turbojet compressor. The turbojet combustor has a bypass with a flow control connected at the inlets...
4170111 Thrust augmentor  
A thrust augmentor for a turbofan, gas turbine engine is disclosed. Techniques for mixing and burning dissimilar density gases in a thrust augmentor are developed. In accordance with one specific...
4145880 Vorbix augmenter configuration with diffuser and vorbix swirler  
An augmenter construction for fan engines in which the fan air and the engine gas are distributed through transition ducts terminating in vortex generators and the fuel rich pilot gas discharges...
4145879 Modified vorbix burner concept  
An augmenter construction for fan engines in which the fan air and engine gas are distributed through transition ducts terminating in vortex generators and the fuel rich pilot gas discharges into...
4145878 Vorbix augmenter configuration  
An arrangement for mixing fan air and engine gas in an engine augmenter which includes transition ducts for diverting some of the fan air into the engine gas annulus, the ducts having vortex...
4134260 Afterburner flow mixing means in turbofan jet engine  
A short length afterburner assembly for a jet propulsion engine having a fan bypass includes cold and hot air cross-over passages and a plurality of flame stabilization swirler vanes associated...
4064692 Variable cycle gas turbine engines  
A design technique, method, and apparatus for varying the bypass ratio and modulating the flow of a gas turbine engine of the bypass type in order to achieve improved mixed mission performance. The...
3871174 Jet engines  
A jet engine comprising a primary flow of hot gas and a secondary air flow hich are separated, up to the entrance to an afterburner duct provided with annular flame-holders by a wall which is...
3812672 SUPERCHARGED EJECTOR RAMJET AIRCRAFT ENGINE  
An aircraft engine which employs the use of a high bypass ratio fan and an ejector in combination with a ramjet, the fan being driven by a gas generator associated with the engine, the ejector...
3788069 LIQUID FUELED ROCKET ENGINE OF THE MAIN CURRENT TYPE HAVING SEPARATE CONTROL NOZZLES OPERATED FROM TURBINE EXHAUST GASES BRANCHED OFF FROM THE ROCKET PROCESS  
A liquid fueled rocket engine of the so-called main current type in which combustion gases are generated in a precombustion chamber and directed in series to a fuel component pump drive turbine and...
3786632 REHEAT SYSTEM FOR A GAS TURBINE ENGINE  
A reheat system for a gas turbine engine is provided with fuel supply means, a plurality of fuel manifolds having fuel distribution holes or nozzles located thereon, fuel/exhaust gas mixing means...
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