US3765178A - Afterburner flameholder - Google Patents

Afterburner flameholder Download PDF

Info

Publication number
US3765178A
US3765178A US00287281A US3765178DA US3765178A US 3765178 A US3765178 A US 3765178A US 00287281 A US00287281 A US 00287281A US 3765178D A US3765178D A US 3765178DA US 3765178 A US3765178 A US 3765178A
Authority
US
United States
Prior art keywords
flame
inlet
afterburner
flameholder
pilot fuel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US00287281A
Other languages
English (en)
Inventor
R Hufnagel
L Pierce
E Sabol
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Application granted granted Critical
Publication of US3765178A publication Critical patent/US3765178A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

Definitions

  • ABSTRACT An afterburner flameholder for an aircraft gas turbine engine is provided with a continuous annular inlet together with a closely adjacent inlet screen to meter gas flow from the turbine exhaust to a plurality of discrete pilot fuel jets within the flameholder.
  • the wake behind the inlet screen is highly turbulent and operates to minimize temperature gradients existing in the inlet flow.
  • the annular inlet communicates with smooth and uniformly flared flow passages through the flameholder thereby inhibiting local variations in flow velocity which heretofore were caused by sudden disruptions in the fiowpath.
  • this invention relates to an afterburner flameholder and, more particularly, to an afterburner flame-holder for inclusion within the gas stream of an aircraft gas turbine engine as part of an afterburning system to provide additional thrust augmentation.
  • the afterburner generally includes a means for dispersing a main flow of fuel together with a flameholder to which the flame may attach.
  • the flameholder reduces locally the velocity of the gas stream in order to sustain the flame which would otherwise blow out.
  • One well known type of flameholder comprises two concentric flame rings arranged to diverge from each other in a downstream direction.
  • the main flow of fuel is dispersed in a manner that allows fuel droplets to impinge upon the outside diverging surfaces of the flameholder wherein the afterburning flame attaches to the trailing edges of the flame rings.
  • pilot fuel may be introduced and sparked to ignite by means of a point source igniter.
  • the pilot flame in turn operates to ignite the main fuel droplets.
  • the pilot fuel jets are generally located intermediate the flame rings suchthat each pilotjet receives gas flow from the turbine exhaust through an individual inlet opening in the leading edge of the flameholder.
  • the temperature of the gas flow into the flameholder generally varies circumferentially around the flameholder. These circumferential temperature gradients are preserved by the conventional system of individual inlet openings for providing gas flow to the pilot fuel jetsand can lead to localized overheating of the flameholder precipitating a condition commonly referred to as hot streaking" wherein the flameholder rapidly deteriorates in the overheated areas.
  • Flashback can be generally described as an upstream propagation of the afterburner flamefront into the interior of the flameholder in the area between the flame rings, and may occur if the velocity of the flow through the flameholder falls off locally below the minimum velocity required to maintain flame attachment.
  • Preignition is not as well understood as flashback, and relates to a sudden spontaneous ignition of the flow in the area between the flame rings of the flameholder.
  • Preignition differs essentially from flashback in that the upstream preignition flame inside the flameholder exists independently of the downstream flame which remains attached to the flame ring trailing edges.
  • Preignition may be a direct result of temperature gradients in the flow through the flameholder. The deleterious effects from flashback and preignition are essentially the same resulting in a premature localized burning of the flameholder components.
  • Flashback and preignition may also result from local velocityvariations of the flow through the flameholder.
  • Such non-uniform velocity profiles can result from abrupt area changes or discontinuities in the flowpath through the flameholder, and are common to conventional flameholders particularly those employing the system of individual inlet openings serving each pilot fuel jet.
  • a gas turbine engine of the type having a compressor, combustor, and turbine in serial flow relation is provided with thrust augmentation by an afterburner.
  • the afterburner includes a flameholder having an inner flame ring,- and an outer flame ring spaced radially outward and concentric to the inner flame ring. Means are further included for introducing a main flow of fuel outside the flame rings together with means for attaching the flame rings to the engine casing.
  • the outer ring in cooperation with the inner ring defines an annular inlet, for receipt of hot gas flow from the turbine, together with an annular outlet.
  • An inlet screen is provided between the inner and outer flame rings closely adjacent the annular inlet for metering the flow between the flame rings and precipitating turbulence in the wake behind the screen.
  • the high turbulence of the wake behind the screen operates to minimize any circumferential temperature gradients in the inflowing gas.
  • Means are included for introducing pilot fuel in discrete jets downstream of the inlet screen.
  • Circumferentially spaced apart airfoil type swirl vanes, radially extending between the inner and outer flame rings, are provided downstream of the pilot fuel injection means together with means for igniting the pilot fuel.
  • the gas-fuel mixture is swirled in a circumferential direction by the swirl vanes in order to provide for a rapid propagation of flame around the entire flameholder.
  • FIG. 1 is a side elevational view partly in crosssection of a gas turbine engine of the turbofan type embodying the afterburner flameholder of this invention.
  • FIG. 2 is an enlarged cross-sectional view of the afterburner flameholder of FIG. 1.
  • FIG. 3 is a cross-sectional view taken along the line 33 of FIG. 2.
  • FIG. 4 is an alternate embodiment for the crosssectional view taken along the line 33 of FIG. 2.
  • a turbofan engine comprising a core engine 12 which generates a hot gas stream for driving a fan turbine 14.
  • the turbine 14 is connected to and drives the rotor 15 of a fan 16 disposed at the inlet end 17 of the engine.
  • the core engine 12 qnd the fan turbine 14 are disposed within an inner casing 18.
  • An elongated cowl, or outer casing 20 defines the engine inlet indicated at 17 and, in combination with the casing 18, defines a duct 22, concentric of the core engine 12.
  • the fan 16 pressurizes an air stream, the outer portion of which passes along the duct 22 and the inner portion of which enters the core engine 12.
  • the air stream is further compressed by a core engine compressor 24 to provide a highly pressurized air stream for supporting combustion of fuel in a combustor 26.
  • Fuel to the combustor 26 is provided by fuel injection means 27 which receives a flow of pressurized fuel through conduit 28 from a source of pressurized fuel (not shown).
  • the hot gas stream thus generated drives a high pressure, core engine turbine 30 which is connected to the rotor of the compressor 24.
  • the hot gas stream passes through the fan turbine 14 and then it is intermixed with a portion of the bypass air from duct 22 entering through an annular passageway 32.
  • Additional thrust augmentation may be provided by the afterburner shown generally at 33. Additional fuel is introduced to the afterburner 33 through fuel inlet means 34 connecting to a source of pressurized fuel (not shown). Means for afterburner flame attachment are provided by flameholder 36, the details of which will be made fully obvious from the discussion below.
  • the hot gas stream exiting from the afterburner 33 is discharged from a nozzle 38 to provide thrust for propulsion of an aircraft.
  • a turbofan engine it could be applied with equal success to other types of gas turbine engines such as the straight turbojet engine.
  • the flameholder 36 comprising an inner frusto conical flame ring 40 and an outer frusto conical flame ring 42.
  • the inner and outer flame rings 40, 42 are arranged in general concentric alignment so as to define an annular inlet 44 and an annular outlet 46 of greater cross-sectional area than the inlet. Radial separation between the flame rings is maintained by a plurality of circumferentially spaced apart and radially extending swirl vanes 48, the profiles of which may be best seen in FIG. 3.
  • the flameholder ring 36 is attached to the inner casing 18 by means of a plurality of circumferentially spaced apart retaining links 50.
  • the outer radial ends of the retaining links 50 are rotatably pinned at pivot 52 to flange elements 54 which are in fixed connection between the inner casing 18 and the outer casing 20.
  • the inner radial end of each retaining link 50 is rotatably pinned at pivot 55 to clevis arrangement 56 extending radially outward ofa piston 58.
  • Piston 58 is disposed within a sleeve 60 which extends through the inner and outer flame rings 40, 42 in generally central alignment with one of the swirl vanes 48.
  • a notch 62 In order to accommodate rotation of the retaining link 50 about the pivot 55, a notch 62 must be provided through the outer flame ring 42, and also the outer radial end 64 of sleeve 60 must be skewed relative to the longitudinal axis of the sleeve.
  • the pivotal feature of the retaining links 50 is provided to accommodate thermal expansion of the flame rings 40, 42 which may result in a radially outward growth of the flameholder 36.
  • the number of retaining links 50 may be varied to suit particular hardware requirements with a minimial requirement of at least three retaining links spaced apart at equal intervals.
  • an inlet screen 68 Adjacent the flameholder annular inlet 44, there is provided an inlet screen 68 preferably comprising a plurality of circumferentially spaced apart and radially extending hollow cylinders 70.
  • the inlet screen 68 meters a pre-determined portion of the inlet gas flow through the confined passages of the flameholder 36.
  • spaced apart hollow cylinders 70 are preferred because the metered flow through the screen remains relatively insensitive to fluctuations in direction of the inlet gas flow.
  • the hollow cylinders of the inlet screen 68 are also convenient to manufacture and easily accommodate to outward radial thermal growth.
  • the afterburner fuel inlet means 34 comprises a plurality of main fuel inlet conduits 74, some of which extend radially through the flameholder 36.
  • Each main fuel inlet conduit 74 includes an aperture 78 closely adjacent the end thereof so as to discharge main jet streams of fuel about the outer surfaces of the flameholder 36.
  • the apertures 78 are spaced radially apart and oriented so as to discharge main jet streams of fuel in directions generally normal to the gas stream.
  • a collar 72 is provided in spaced apart relation around the main fuel inlet conduits 74 to permit outward radial thermal expansion of the flameholder 36 without interference from the main fuel inlet conduits.
  • a pilot fuel conduit 76 terminates between the inner and outer flame rings 40, 42.
  • Each pilot fuel conduit 76 includes two circumferentially spaced apart apertures 77, 77', which may be best seen in FIGS. 3 and 4.
  • the apertures 77, 77' are arranged to direct two divergent jet streams of pilot fuel, each stream of which flows through the nozzle defined by two adjacent swirl vanes 48.
  • the pilot fuel conduits 76 need only be located adjacent the leading edges of every other swirl vane 48 in order to provide ajet stream of pilot fuel to each nozzle.
  • lgniter 80 provides a point source of spark to ignite the pilot fuel.
  • the swirl vanes 48 which generally comprise a frusto conical main body portion 82.
  • An integral tail portion 84 extends rearwardly and circumferentially from the main body portion 82.
  • Side walls 86, 88 of the integral tail portion 84 converge rearwardly from tangential intersection with the frusto conical main body 82 and intersect at a swirl vane trailing edge 90.
  • the throat width A of each nozzle between adjacent swirl vanes 48 is selected to achieve the minimum gas flow velocity therethrough that will maintain flame attachment to the trailing edges 90.
  • the afterburner may be lit by first introducing pilot fuel through conduit 76, whereupon the pilot fuel is sparked to ignite by igniter 80.
  • Inlet screen 68 meters a predetermined portion of the total gas flow through the annular inlet 44 so as to achieve the desired stoichiometric ratio of fuel to air.
  • the hollow cylinders or rods 70 provide for a highly predictable and uniform metered flow through theflameholder.
  • the temperature of the gas flow into the flameholder 36 may vary circumferentially around the flameholder. Such circumferential temperature gradients can precipitate hot streaks within the flameholder leading to rapid localized deterioration of the flameholder.
  • the wake behind the inlet screen 68 provides a high level of turbulence so as to thoroughly mix the incoming gas flow, thereby minimizing the circumferential temperature gradients which can lead to the premature deterioration of the flameholder. Therefore, the continuous annular inlet feature of the flameholder of this invention coupled with the inlet screen provides a marked advantage over conventional flameholders having individual discrete inlet openings servicing each pilot fuel jet.
  • the turbulent wake behind the inlet screen 68 also provides for a high degree of mixing and dispersing of pilot fuel within the hot incoming gas.
  • This highly uniform gas-fuel mixture flows downstream between the swirl vanes 48 to the flame zone which is desirably maintained behind the swirl vane trailing edges 90.
  • the gas-fuel mixture is swirledin a circumferential direction in order to provide for a rapid propagation of flame around the entire flameholder from the initial point of spark at igniter 80.
  • Main fuel is ignited by the annular pilot flame in a conventional manner.
  • flashback is an upstream propagation of the afterburner flame front into the interior passages of the flameholder. Flashback may occur if the velocity of the fuel-gas mixture between the swirl vanes 48 falls off below the minimum speed required to maintain flame attachment at the swirl vane trailing edges 90.
  • preignition is'not as well understood as flashback and relates to a sudden spontaneous ignition of the fuel-gas mixture in an area upstream of the swirl vane trailing edges 90. Preignition differs essentially from flashback in that the upstream preignition flame inside the flameholder is separate and distinct, existing independently of the downstream flame attached to the swirl vane trailing edges 90.
  • Preignition may be a direct result of the circumferential temperature gradients previously discussed. Therefore, the probability of preignition occurring in the flameholder of this invention is believed to be minimized by the thorough mixing effect of the highly turbulent wake behind the inlet screen 68.
  • the velocity profile be kept uniform and predictable over all cross-sections taken between the plane of pilot fuel injection at inlet conduit 76 and the plane defined by the swirl vane trailing edges 90.
  • the flow paths through the afterburner are designed with abrupt area changes or discontinuities as has been the case for conventional afterburner flameholders, then local perturbations and eddies will develop and disrupt the uniform nature of the velocity profiles. These preturbations and eddies will cause the velocity of the gas-fuel mixture approaching the swirl vane trailing edges to fall off locally below the minimum velocity required to maintain flame attachment at the trailing edges. In such cases the afterburner flamefront will propagate upstream into the interior passages of the flameholder at those areas of flow velocity disruption causing localized overheating and burning of the flameholder components.
  • the flow passages of the flameholder of this invention have been specifically designed to be smooth and uniformly flared with no sudden area changes or discontinuities in the passageways between the plane of pilot fuel injection at inlet conduit 76 and the plane defined by the swirl vane trailing edges 90.
  • the high turbulence of the wake behind the inlet screen 68 becomes substantially exhausted before reaching the swirl vane trailing edges 90 so as to provide a substantially uniform velocity profile at the trailing edges 90.
  • Swirl vanes 48 are essentially airfoil shaped with gradually contoured sides presenting no sharp discontinuities to the fuel-gas flow therethro'ugh which could precipitate localized flashback or preignition.
  • the geometric configuration is simple and provides for a readily predictable flow between the swirl vanes. The configuration also lends itself for economical low cost tooling and manufacture.
  • FIG. 4 there is shown a slight modiflcation of the swirl vanes 48.
  • a sharp integral leading edge portion 92 has been included forward of the main body portion 82 and includes sidewalls 96, 98 converging forward from tangential intersection with the main body 82, thereby streamlining the aerodynamic profile of each swirl vane 48.
  • sidewall 86 of the integral tail portion has been extended rearwardly and circumferentially at 94 beyond the line of intersection 90 of the converging sidewalls 86, 88.
  • the angle of discharge of the gas-fuel mixture from swirl vanes 48 may therefore be made to more nearly approximate the circumferential direction, thereby reducing the overall time required for flame propagation around the annular flameholder. Also, convective cooling of the vane trailing edges is further facilitated by this arrangement.
  • the swirl vanes 48 may be of any suitable airfoil cross-section so long as a prescribed and predictable flow can be achieved between the vanes.
  • the inlet screen 68 could alternatively be a reticulate configuration. Therefore, having described preferred embodiments of the invention, though not exhaustive of all possible equivalents, what is desired to be secured by letters patent is claimed below.
  • an afterburner comprising:
  • an outer flame ring spaced radially outward and concentric to the inner flame ring, which in cooperation with the inner flame ring defines an annular inlet for receipt of hot gas flow from the turbine, together with an annular outlet;
  • attaching means comprise a plurality of retaining links pivotally connected at one end to the engine casing;
  • the inner and outer flame rings are conical frustums cooperatively arranged to define an annular rearwardly diverging passageway.
  • the inlet screen comprises a plurality of circumferentially spaced cylinders extending radially between the inner and outer flame rings.
  • each swirl vane comprises a generally frusto conical main body portion with an integral tail portion extending rearwardly and circumferentially from the main body portion with the sidewalls of the integral tail portion converging rearwardly from tangential intersection with the frusto conical main body into intersection at the swirl vane trailing edge.
  • each swirl vane includes a sharp integral leading edge portion extending forward of the main body portion with the sidewalls of the integral leading edge portion converging forwardly from tangential intersection with the frusto conical main body into intersection at the swirl vane leading edge and wherein:
  • a sidewall of the integral tail portion extends rearwardly and circumferentially beyond the line of intersection of the converging tail portion sidewalls.
  • the pilot fuel means includes an inlet conduit terminating between the flame rings at a point closely adjacent the leading edge of a swirl vane and having two spaced apart apertures for directing individual jets of pilot fuel on each side of the adjacent swirl vane, and wherein:
  • the main fuel means includes a plurality of inlet conduits terminating radially outward and inward of both flame rings, each conduit ofwhich includes an aperture for directing ajet of main fuel outside the flame rings.
  • a flameholder comprising:

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Exhaust Gas After Treatment (AREA)
US00287281A 1972-09-08 1972-09-08 Afterburner flameholder Expired - Lifetime US3765178A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US28728172A 1972-09-08 1972-09-08

Publications (1)

Publication Number Publication Date
US3765178A true US3765178A (en) 1973-10-16

Family

ID=23102221

Family Applications (1)

Application Number Title Priority Date Filing Date
US00287281A Expired - Lifetime US3765178A (en) 1972-09-08 1972-09-08 Afterburner flameholder

Country Status (8)

Country Link
US (1) US3765178A (xx)
JP (1) JPS4992423A (xx)
BE (1) BE804377A (xx)
CA (1) CA958551A (xx)
DE (1) DE2344630A1 (xx)
FR (1) FR2199062A1 (xx)
GB (1) GB1426784A (xx)
IT (1) IT993117B (xx)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3931707A (en) * 1975-01-08 1976-01-13 General Electric Company Augmentor flameholding apparatus
FR2330867A1 (fr) * 1975-11-04 1977-06-03 Gen Electric Stabilisateur de flamme amovible
US4125998A (en) * 1976-05-13 1978-11-21 Societe Nationale Et De Construction De Moteurs D'aviation Device for igniting fuel injected into a rapidly flowing gaseous medium
US4203285A (en) * 1978-02-06 1980-05-20 The United States Of America As Represented By The Secretary Of The Air Force Partial swirl augmentor for a turbofan engine
US4490973A (en) * 1983-04-12 1985-01-01 The United States Of America As Represented By The Secretary Of The Air Force Flameholder with integrated air mixer
US4592200A (en) * 1983-09-07 1986-06-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation - S.N.E.C.M.A. Turbo-jet engine afterburner system
US4815283A (en) * 1987-06-25 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Afterburner flameholder construction
US4887425A (en) * 1988-03-18 1989-12-19 General Electric Company Fuel spraybar
US4893468A (en) * 1987-11-30 1990-01-16 General Electric Company Emissions control for gas turbine engine
US4899539A (en) * 1988-01-14 1990-02-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Flow mixer and flame stabilizer for a turbofan engine
US4901527A (en) * 1988-02-18 1990-02-20 General Electric Company Low turbulence flame holder mount
US5076062A (en) * 1987-11-05 1991-12-31 General Electric Company Gas-cooled flameholder assembly
US5157917A (en) * 1991-05-20 1992-10-27 United Technologies Corporation Gas turbine engine cooling air flow
EP0620404A1 (en) * 1993-04-15 1994-10-19 General Electric Company Removable afterburner flameholder
US5768886A (en) * 1995-09-29 1998-06-23 National Science Council Twin-plate flameholder construction
FR2873168A1 (fr) * 2004-07-16 2006-01-20 Snecma Moteurs Sa Turboreacteur comprenant une chambre de post-combustion a allumage securise
EP1873387A2 (en) * 2006-06-29 2008-01-02 General Electric Company Purged flameholder fuel shield
US20080098740A1 (en) * 2006-10-31 2008-05-01 Brian Benscoter Roberts Method and apparatus for assembling an augmenter in gas turbine engines
US7565804B1 (en) * 2006-06-29 2009-07-28 General Electric Company Flameholder fuel shield
CN103090411A (zh) * 2011-11-04 2013-05-08 通用电气公司 具有用于减少在空气流中的尾流的文丘里管的燃烧系统
US20180320899A1 (en) * 2017-05-08 2018-11-08 General Electric Company Coupling method and structure for a propulsion system hot section
US10168050B2 (en) 2014-04-30 2019-01-01 Ihi Corporation Afterburner and aircraft engine
US10197011B2 (en) 2014-04-30 2019-02-05 Ihi Corporation Afterburner and aircraft engine
US10634352B2 (en) * 2013-03-08 2020-04-28 Rolls-Royce North American Technologies Inc. Gas turbine engine afterburner
CN115164234A (zh) * 2022-05-12 2022-10-11 中国航发四川燃气涡轮研究院 加力燃烧室火焰稳定器
FR3136016A1 (fr) * 2022-05-30 2023-12-01 Safran Aircraft Engines Anneau accroche-flammes pour postcombustion de turboreacteur comprenant un conduit pour chauffer un segment angulaire de l'anneau

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6125813A (en) * 1997-06-09 2000-10-03 Patrick Power Products, Inc. Prechamber combustion for a rotary diesel engine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2296023A (en) * 1941-03-03 1942-09-15 Northrop Aircraft Inc Burner
US2679137A (en) * 1947-10-21 1954-05-25 Power Jets Res & Dev Ltd Apparatus for burning fuel in a fast moving gas stream
US3054259A (en) * 1962-09-18 Combustion apparatus
US3156094A (en) * 1962-11-21 1964-11-10 Gen Electric Catalytic ignition means for a jet engine thrust augmentation system
US3355885A (en) * 1964-11-19 1967-12-05 Rolls Royce Prime mover ignition device

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3054259A (en) * 1962-09-18 Combustion apparatus
US2296023A (en) * 1941-03-03 1942-09-15 Northrop Aircraft Inc Burner
US2679137A (en) * 1947-10-21 1954-05-25 Power Jets Res & Dev Ltd Apparatus for burning fuel in a fast moving gas stream
US3156094A (en) * 1962-11-21 1964-11-10 Gen Electric Catalytic ignition means for a jet engine thrust augmentation system
US3355885A (en) * 1964-11-19 1967-12-05 Rolls Royce Prime mover ignition device

Cited By (38)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3931707A (en) * 1975-01-08 1976-01-13 General Electric Company Augmentor flameholding apparatus
FR2330867A1 (fr) * 1975-11-04 1977-06-03 Gen Electric Stabilisateur de flamme amovible
US4064691A (en) * 1975-11-04 1977-12-27 General Electric Company Cooling of fastener means for a removable flameholder
US4125998A (en) * 1976-05-13 1978-11-21 Societe Nationale Et De Construction De Moteurs D'aviation Device for igniting fuel injected into a rapidly flowing gaseous medium
US4203285A (en) * 1978-02-06 1980-05-20 The United States Of America As Represented By The Secretary Of The Air Force Partial swirl augmentor for a turbofan engine
US4490973A (en) * 1983-04-12 1985-01-01 The United States Of America As Represented By The Secretary Of The Air Force Flameholder with integrated air mixer
US4592200A (en) * 1983-09-07 1986-06-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation - S.N.E.C.M.A. Turbo-jet engine afterburner system
US4815283A (en) * 1987-06-25 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Afterburner flameholder construction
US5076062A (en) * 1987-11-05 1991-12-31 General Electric Company Gas-cooled flameholder assembly
US4893468A (en) * 1987-11-30 1990-01-16 General Electric Company Emissions control for gas turbine engine
US4899539A (en) * 1988-01-14 1990-02-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Flow mixer and flame stabilizer for a turbofan engine
US4901527A (en) * 1988-02-18 1990-02-20 General Electric Company Low turbulence flame holder mount
US4887425A (en) * 1988-03-18 1989-12-19 General Electric Company Fuel spraybar
US5157917A (en) * 1991-05-20 1992-10-27 United Technologies Corporation Gas turbine engine cooling air flow
EP0620404A1 (en) * 1993-04-15 1994-10-19 General Electric Company Removable afterburner flameholder
US5768886A (en) * 1995-09-29 1998-06-23 National Science Council Twin-plate flameholder construction
FR2873168A1 (fr) * 2004-07-16 2006-01-20 Snecma Moteurs Sa Turboreacteur comprenant une chambre de post-combustion a allumage securise
EP1621817A1 (fr) * 2004-07-16 2006-02-01 Snecma Moteurs Chambre de post-combustion à allumage sécurisé
EP1873387A2 (en) * 2006-06-29 2008-01-02 General Electric Company Purged flameholder fuel shield
EP1873459A3 (en) * 2006-06-29 2015-08-05 General Electric Company Flameholder fuel-shield
US20090113894A1 (en) * 2006-06-29 2009-05-07 General Electric Company Purged flameholder fuel shield
US7565804B1 (en) * 2006-06-29 2009-07-28 General Electric Company Flameholder fuel shield
KR101378179B1 (ko) 2006-06-29 2014-03-25 제너럴 일렉트릭 캄파니 터보팬 엔진용 재연소기
US7581398B2 (en) * 2006-06-29 2009-09-01 General Electric Company Purged flameholder fuel shield
EP1873387A3 (en) * 2006-06-29 2012-03-14 General Electric Company Purged flameholder fuel shield
US7568346B2 (en) * 2006-10-31 2009-08-04 General Electric Company Method and apparatus for assembling a flameholder for an augmenter
US20080098740A1 (en) * 2006-10-31 2008-05-01 Brian Benscoter Roberts Method and apparatus for assembling an augmenter in gas turbine engines
CN103090411A (zh) * 2011-11-04 2013-05-08 通用电气公司 具有用于减少在空气流中的尾流的文丘里管的燃烧系统
US9267687B2 (en) 2011-11-04 2016-02-23 General Electric Company Combustion system having a venturi for reducing wakes in an airflow
CN103090411B (zh) * 2011-11-04 2016-05-18 通用电气公司 具有用于减少在空气流中的尾流的文丘里管的燃烧系统
US10634352B2 (en) * 2013-03-08 2020-04-28 Rolls-Royce North American Technologies Inc. Gas turbine engine afterburner
US10168050B2 (en) 2014-04-30 2019-01-01 Ihi Corporation Afterburner and aircraft engine
US10197011B2 (en) 2014-04-30 2019-02-05 Ihi Corporation Afterburner and aircraft engine
US10563868B2 (en) * 2017-05-08 2020-02-18 General Electric Company Coupling method and structure for a propulsion system hot section
US20180320899A1 (en) * 2017-05-08 2018-11-08 General Electric Company Coupling method and structure for a propulsion system hot section
CN115164234A (zh) * 2022-05-12 2022-10-11 中国航发四川燃气涡轮研究院 加力燃烧室火焰稳定器
CN115164234B (zh) * 2022-05-12 2023-06-13 中国航发四川燃气涡轮研究院 加力燃烧室火焰稳定器
FR3136016A1 (fr) * 2022-05-30 2023-12-01 Safran Aircraft Engines Anneau accroche-flammes pour postcombustion de turboreacteur comprenant un conduit pour chauffer un segment angulaire de l'anneau

Also Published As

Publication number Publication date
DE2344630A1 (de) 1974-03-14
CA958551A (en) 1974-12-03
BE804377A (fr) 1974-01-02
JPS4992423A (xx) 1974-09-03
GB1426784A (en) 1976-03-03
IT993117B (it) 1975-09-30
FR2199062A1 (xx) 1974-04-05

Similar Documents

Publication Publication Date Title
US3765178A (en) Afterburner flameholder
US3931707A (en) Augmentor flameholding apparatus
US5020318A (en) Aircraft engine frame construction
CA2961771C (en) Closed trapped vortex cavity pilot for a gas turbine engine augmentor
US3299632A (en) Combustion chamber for a gas turbine engine
US8011188B2 (en) Augmentor with trapped vortex cavity pilot
CA2551711C (en) Augmentor radial fuel spray bar with counterswirling heat shield
US7762073B2 (en) Pilot mixer for mixer assembly of a gas turbine engine combustor having a primary fuel injector and a plurality of secondary fuel injection ports
US6295801B1 (en) Fuel injector bar for gas turbine engine combustor having trapped vortex cavity
US7437876B2 (en) Augmenter swirler pilot
US5396761A (en) Gas turbine engine ignition flameholder with internal impingement cooling
US5813221A (en) Augmenter with integrated fueling and cooling
EP1605207B1 (en) Thrust augmentor for gas turbine engines
CA2567533C (en) Externally fueled trapped vortex cavity augmentor
US20070028618A1 (en) Mixer assembly for combustor of a gas turbine engine having a main mixer with improved fuel penetration
US3747345A (en) Shortened afterburner construction for turbine engine
US20070028595A1 (en) High pressure gas turbine engine having reduced emissions
US3498055A (en) Smoke reduction combustion chamber
US4134260A (en) Afterburner flow mixing means in turbofan jet engine
US8272219B1 (en) Gas turbine engine combustor having trapped dual vortex cavity
JP4997018B2 (ja) 一次燃料噴射器及び複数の二次燃料噴射ポートを有するガスタービンエンジン燃焼器のミキサ組立体のためのパイロットミキサ
EP2400221B1 (en) Ejector purge of cavity adjacent exhaust flowpath
US4145880A (en) Vorbix augmenter configuration with diffuser and vorbix swirler
US3372541A (en) Gas turbine engine combustion chamber
BR102017006418A2 (pt) Closed rebound vessel apparatus and a pilot ignition supply method for a gas turbine engine rider