| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060761000 | Having afterburner | 20 |
| 20090260365 | Augmentor Spray Bar Mounting - A gas turbine engine augmentor has a centerbody within a gas flowpath from upstream to downstream. The augmentor has upstream and downstream shell sections, a downstream rim of the upstream shell section meeting an upstream rim of the downstream shell section shell section. A plurality of vanes are positioned in the gas flowpath outboard of the centerbody. An augmentor spray bar fuel conduit extends through the centerbody and a first of the vanes to deliver fuel to the centerbody. A seal is mounted to the spray bar and positioned in a recess extending from at least one of the downstream rim of the upstream shell section and upstream rim of the downstream shell section shell section. The seal has a first portion and a second portion engaging the first portion in a backlocked interfitting. | 10-22-2009 |
| 20120102961 | Side-Initiated Augmentor for Engine Applications - A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath. | 05-03-2012 |
| 20130091849 | AUGMENTOR SPRAY BAR WITH TIP SUPPORT BUSHING - An augmentor for a gas turbine engine includes an augmentor spray bar with a spray bar outlet, and an augmentor spray bar tip. The spray bar tip includes a tip body, a tip bushing and a tip support strut. The tip body includes a first flow passage extending therethrough between a tip inlet and a tip outlet, wherein the tip inlet is connected to the spray bar outlet. The tip bushing includes a bushing bore. The tip body extends through the bushing bore defining a second flow passage between the tip body and the tip bushing. The tip support strut connects the tip body to the tip bushing across the second flow passage. | 04-18-2013 |
| 20130318980 | SPRAYBAR FACE SEAL RETENTION ARRANGEMENT - An example turbomachine assembly includes a plurality of fuel spraybars spaced about a turbine exhaust inner case of the turbomachine. At least one fuel injector assembly is associated with each of the fuel spraybars. The at least one fuel injector assembly may include a fuel nozzle having a fuel delivery conduit. The at least one fuel injector assembly includes a seal member that is biased away from the fuel nozzle in a direction. The fuel nozzle is configured to limit movement of the seal member in the direction. | 12-05-2013 |
| 20140000268 | IGNITER FOR A TURBOMACHINE AND MOUNTING ASSEMBLY THEREFORE | 01-02-2014 |
| 20140338348 | ROTARY PULSE DETONATION ENGINE - This invention relates to devices for discharging high pressure exhaust, and in particular to pulse detonation engines. More specifically, the invention describes a rotary pulse detonation engine having a rotary valve system. The rotary valve includes a generally-triangular rotor having rotor tips within a rotor chamber having trochoid inner end surfaces and side surfaces. The rotor defines three working chambers defined by the rotor tips contacting the rotor surfaces. In operation, the rotor tips move in a circumferential direction around the rotor chamber as the rotor spins. During operation, each of the working chambers will sequentially pass through an intake interval, compression interval, expansion interval, and an exhaust interval to create and detonate compressed fuel air mixtures for effective release to an exhaust chamber and nozzle thereby creating a pulsed detonation sequence. | 11-20-2014 |
| 20150316000 | GAS TURBINE ENGINE SYSTEMS AND METHODS INVOLVING ENHANCED FUEL DISPERSION - Gas turbine engine systems and methods involving enhanced fuel dispersion are provided. In this regard, a representative method for operating a gas turbine engine includes: providing a gas path through the engine; introducing a spray of fuel along the gas path downstream of a turbine of the engine; and impinging the spray of fuel with a relatively higher velocity flow of air such that atomization of the fuel is increased. | 11-05-2015 |
| 060762000 | Having oxidizer bypassed to afterburner feature | 1 |
| 20150121886 | GAS TURBINE ENGINE AFTERBURNER - An afterburner is disclosed for use with a gas turbine engine and, in one form, is structured to receive a bypass air. The afterburner can be situated in a bypass duct and can be a toroidal combustor or a can combustor. In one embodiment, the afterburner includes a combustor arranged to receive bypass air and a plurality of vanes distributed downstream of a turbine of the gas turbine engine. The vanes can include one or more exit apertures through which hot combustion flow from the afterburner combustor can be injected. The exit apertures can be protrusions or slots in some forms. In one embodiment, a cooling passage is arranged around the exit apertures. An upstream vane portion can be positioned to inject fuel to be combusted via interaction with hot flow that is discharged through the exit apertures. | 05-07-2015 |
| 060765000 | Particular flame holder structure | 10 |
| 20090056340 | AUGMENTOR WITH TRAPPED VORTEX CAVITY PILOT - A gas turbine engine augmentor includes an annular trapped vortex cavity pilot having a cavity forward wall, a cavity radially outer wall, and a cavity aft wall, an annular cavity therebetween, and cavity fuel injector tubes operably disposed through the outer wall into the cavity. Circumferentially spaced apart radial flameholders with integral spraybars and/or radial spraybars interdigitated with the radial flameholders radially inwardly into an exhaust flowpath of the augmentor just forward and upstream of the trapped vortex cavity pilot at a radially outer portion of a combustion zone of the exhaust flowpath. An annular trapped dual vortex cavity pilot version is operable for producing trapped dual counter-rotating inner and outer vortices of fuel and air mixtures. | 03-05-2009 |
| 20090113894 | 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 therefrom to conform with a supporting outer shell of the flameholder. | 05-07-2009 |
| 20090260366 | FLAME HOLDER FOR AN AFTERBURNER DUCT OF A JET ENGINE WITH A SPACER SHOE, AFTERBURNER DUCT, AND JET ENGINE COMPRISING AN AFTERBURNER DUCT - The invention relates to a flame holder ( | 10-22-2009 |
| 20100218505 | AFTERBURNER CHAMBER FOR A TURBOMACHINE - An afterburner chamber ( | 09-02-2010 |
| 20110067407 | FLAME-HOLDER DEVICE COMPRISING AN ARM SUPPORT AND A HEAT-PROTECTION SCREEN THAT ARE IN ONE PIECE - A flame-holder device for the afterburning of a bypass turbojet, said turbojet comprising first and second internal annular casings, defining a passageway for a main flow, and an external annular casing defining with said first internal annular casing a passageway for a bypass flow, comprising: | 03-24-2011 |
| 20140360197 | AFTERBURNER AND AIRCRAFT ENGINE - An aircraft engine includes an afterburner which has a flame stabilizer. The flame stabilizer maintains a flame generated from a mixed gas of a combustion gas and air. The flame stabilizer includes multiple gutters each configured to generate a flame stabilization area for the flame on its downstream side. Each gutter is formed from: a curved apex section having a stagnation point; and flat plate-shaped side surface sections integrally formed on the respective two sides of the apex section. Each gutter has a V-shaped cross-sectional shape which is opened to the downstream side. At least one through-hole is formed only in each side surface section of each gutter. | 12-11-2014 |
| 20160069298 | VARIABLE ORIFICE JET FOR A TURBINE ENGINE - A fuel delivery system is provided for a turbine engine. This fuel delivery system includes a variable orifice jet configured to spray fuel received from a spray bar fuel conduit. The variable orifice jet includes a flexible body and a pintle that extends through a sidewall of the flexible body. An area of an orifice between the sidewall and the pintle is variable. | 03-10-2016 |
| 20160169518 | INJECTING APPARATUS WITH REHEAT COMBUSTOR AND TURBOMACHINE | 06-16-2016 |
| 20160169519 | INJECTOR APPARATUS AND REHEAT COMBUSTOR | 06-16-2016 |
| 20160169520 | INJECTOR APPARATUS WITH REHEAT COMBUSTOR AND TURBOMACHINE | 06-16-2016 |
| 060766000 | Particular liner or casing structure | 2 |
| 20090077978 | Self-aligning liner support hanger - A self-aligning hanger for use in a gas turbine engine exhaust system comprises a first bracket, a second bracket, a rod, a first ball joint and a second ball joint. The first bracket is for connecting to an exhaust duct of the gas turbine exhaust system. The second bracket is for connecting to an exhaust duct liner of the gas turbine exhaust system. The rod extends between the first bracket and the second bracket. The first ball joint connects a first end of the rod with the first bracket. The second ball joint connects a second end of the rod with the second bracket. | 03-26-2009 |
| 20140250895 | MODULATED EJECTOR COOLING - A cooling air flow ejector has a primary nozzle position to entrain air from a secondary nozzle. Mixed air is provided into a downstream flow conduit to be directed to an exhaust liner for a gas turbine engine. A variable area device controls a volume of air passing through a primary nozzle. A control for the variable area device to control the size of an orifice within the variable area device controls the volume of air reaching the exhaust liner to be cooled. | 09-11-2014 |
