EP0142389B1 - Anneau-brûleur pour postcombustion de moteur à réaction - Google Patents

Anneau-brûleur pour postcombustion de moteur à réaction Download PDF

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Publication number
EP0142389B1
EP0142389B1 EP84401726A EP84401726A EP0142389B1 EP 0142389 B1 EP0142389 B1 EP 0142389B1 EP 84401726 A EP84401726 A EP 84401726A EP 84401726 A EP84401726 A EP 84401726A EP 0142389 B1 EP0142389 B1 EP 0142389B1
Authority
EP
European Patent Office
Prior art keywords
ring
limb
burner
flows
burner ring
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
Application number
EP84401726A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0142389A1 (fr
Inventor
René Alain Benoist
Michel Robert Clauzel
Roger Alfred Jules Vandenbroucke
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0142389A1 publication Critical patent/EP0142389A1/fr
Application granted granted Critical
Publication of EP0142389B1 publication Critical patent/EP0142389B1/fr
Expired legal-status Critical Current

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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

  • the invention relates to a burner ring for afterburning of a jet engine, in particular for a heating system of a turbofan engine, said system being placed behind the wall separating the two streams and comprising a stabilizing ring for approximately V-shaped section flame containing a circular fuel injection ramp flowing against the current through openings provided at the tip of the V.
  • Certain multiflux military engines equipped with a heating system on the two flows, have a very reduced master torque. They may include one or more burner rings used for post-combustion proper and for heating the secondary cold flow. Generally one of the afterburner rings is located at the confluence of the two streams, just behind the conical wall separating them.
  • the burner ring includes a V-section flame stabilizing ring containing a circular fuel injection ramp flowing counter-current through openings made at the tip of the V.
  • the stabilizing ring As a result of the position of the stabilizing ring, its wings are subjected to very different temperatures.
  • the external wing is bathed by the secondary air flow, the temperature of which does not exceed 200 ° C. while the internal wing is subjected to the temperature of the gas leaving the turbine, of the order of 850 ° C.
  • French patent application 2,186,608 proposes a solution to the problem of overheating by arranging, at a certain distance upstream from the burner ring, an annular member called an anvil, against which the jets emitted by the holes provided in the ramp.
  • the mixture of gas and pulverized fuel thus produced, penetrates through the openings surrounding the jets and provided in the stabilizing ring, in the space surrounding the ramp in the ring and protects the latter against the heat of the flame.
  • the layers of fog are uniformly charged with sprayed fuel and wet the outer surface of the stabilizing ring which avoids hot spots and excessive deformation.
  • the device described does not, however, avoid stresses in the ring, which adversely affects its mechanical strength.
  • the main purpose of the anvil is to obtain a uniform spraying of the fuel into the air stream and better flame stability.
  • the invention proposes to remedy the constraints arising in the stabilizing ring by dissociating the two wings and allowing them to expand freely separately, each wing being held by a device articulated to the wall separating the two flows.
  • the invention is remarkable in that the flame stabilizing ring is formed by two independent parts, each of these parts constituting a wing of the V, and in that articulated support means are provided at the end of the partition wall flows to maintain each of the parts of the stabilizing ring.
  • the burner ring 3 comprises an injection ramp 5, pierced with orifices 6 for injecting fuel, against the flow of the primary and secondary air streams, a flame stabilizing ring 7 located upstream of the ramp and surrounding it.
  • the stabilizing ring has a section approximately in V, the point of the V being directed upstream of the current.
  • the stabilizing ring is formed by two independent parts 8 and 9, each of these parts constituting a wing of the V.
  • the two adjacent ends of the wings leave between them a continuous annular slot 10 allowing passage fuel jets emitted by the rail 5.
  • the burner ring 3 is held on the conical flow separation wall 4 by articulated support means 11.
  • the outer 8 and inner 9 wings are suspended from the conical wall 4 by bent levers 12, by means of welded yokes 13 and 14 respectively on the wings 8 and 9, arranged in the same axial planes and distributed uniformly along the wings.
  • the levers 12 have two arms 15 and 16 of unequal length.
  • the shortest arm 16 ends in a double yoke 16a which cooperates by means of a link 17 being articulated to the double yokes 16a and 14 by two axes 18 and 19 (see also Figure 4).
  • the elbow formed by the arms 15 and 16 comprises a bore which receives the axis 20 now in an articulated manner the yoke 13 welded to the outer wing 8.
  • the free end of the longest arm 15 carries a bore cooperating via a pin 21 with a yoke 22 fixed on the external surface of the wall 4.
  • the injection ramp 5 is fixed from place to place along the wing by lugs 23 and rivets 24 to the outer wing 8 of the ring.
  • the outer wing 8 immersed in the secondary air flow at low temperature, exhibits low thermal expansion and its dimensional characteristics vary little.
  • the injection ramp 5 which is integral with it will not undergo any significant displacement capable of modifying the direction of the jets and will make it possible to maintain a reasonable width of the annular slot 10 despite the relatively large expansion of the internal wing 9.
  • the continuous slot 10 of the burner ring according to the invention will optionally allow the use of an anvil ring as described in French patent application 2 186 608.
  • the removal of the partitions separating the openings surrounding the jets as described in the cited patent prevents the deformation of this relatively small area and improves the passage of the mixture of gas and fuel sprayed into the space surrounding the ramp 5 in the stabilizing ring 7 and protects the ramp against the heat of the flame.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Processes For Solid Components From Exhaust (AREA)
EP84401726A 1983-09-07 1984-08-29 Anneau-brûleur pour postcombustion de moteur à réaction Expired EP0142389B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8314249A FR2551500B1 (fr) 1983-09-07 1983-09-07 Anneau-bruleur pour postcombustion de moteur a reaction
FR8314249 1983-09-07

Publications (2)

Publication Number Publication Date
EP0142389A1 EP0142389A1 (fr) 1985-05-22
EP0142389B1 true EP0142389B1 (fr) 1986-10-01

Family

ID=9292032

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84401726A Expired EP0142389B1 (fr) 1983-09-07 1984-08-29 Anneau-brûleur pour postcombustion de moteur à réaction

Country Status (6)

Country Link
US (1) US4592200A (enrdf_load_stackoverflow)
EP (1) EP0142389B1 (enrdf_load_stackoverflow)
JP (1) JPS60155827A (enrdf_load_stackoverflow)
DE (1) DE3460874D1 (enrdf_load_stackoverflow)
FR (1) FR2551500B1 (enrdf_load_stackoverflow)
IL (1) IL72744A (enrdf_load_stackoverflow)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4765136A (en) * 1985-11-25 1988-08-23 United Technologies Corporation Gas turbine engine augmentor
FR2626044A1 (fr) * 1988-01-14 1989-07-21 Snecma Melangeur de flux a section variable avec stabilisateur de rechauffe integre pour turboreacteur double flux
US4901527A (en) * 1988-02-18 1990-02-20 General Electric Company Low turbulence flame holder mount
US5103638A (en) * 1990-01-29 1992-04-14 Rolls-Royce Inc. Mounting arrangement
US5680754A (en) * 1990-02-12 1997-10-28 General Electric Company Compressor splitter for use with a forward variable area bypass injector
US5155993A (en) * 1990-04-09 1992-10-20 General Electric Company Apparatus for compressor air extraction
US5231825A (en) * 1990-04-09 1993-08-03 General Electric Company Method for compressor air extraction
US5127224A (en) * 1991-03-25 1992-07-07 United Technologies Corporation Spray-ring mounting assembly
FR2687734B1 (fr) * 1992-02-26 1994-08-26 Snecma Dispositif accroche-flammes a geometrie variable destine a etre utilise dans le dispositif post-combustion d'une turbomachine.
US5768886A (en) * 1995-09-29 1998-06-23 National Science Council Twin-plate flameholder construction
CA2394397A1 (en) * 1999-12-15 2001-06-21 Osaka Gas Co., Ltd. Fluid distributor, burner device, gas turbine engine, and cogeneration system
FR2869953B1 (fr) * 2004-05-05 2008-07-04 Snecma Moteurs Sa Dispositif d'alimentation en air et en carburant d'un anneau-bruleur dans une chambre de postcombustion
JP5625585B2 (ja) * 2010-07-27 2014-11-19 株式会社Ihi アフタバーナ及び航空機エンジン
GB201013723D0 (en) * 2010-08-17 2010-09-29 Rolls Royce Plc Manifold mounting arrangement
CN104439634B (zh) * 2014-11-07 2016-03-30 沈阳黎明航空发动机(集团)有限责任公司 一种防止环形v槽稳定器焊接变形的装置及其使用方法
FR3032519B1 (fr) * 2015-02-10 2017-02-24 Herakles Dispositif accroche-flamme
CN113883549B (zh) * 2021-12-08 2022-02-22 中国航发沈阳发动机研究所 一种兼顾雷达隐身的火焰稳定器
US11939922B2 (en) * 2022-08-19 2024-03-26 Pratt & Whitney Canada Corp. Fuel assembly for a gas turbine engine

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2799991A (en) * 1954-03-05 1957-07-23 Earl W Conrad Afterburner flame stabilization means
US2875580A (en) * 1957-04-16 1959-03-03 Westinghouse Electric Corp Flameholding apparatus
US3102392A (en) * 1959-04-21 1963-09-03 Snecma Combustion equipment for jet propulsion units
FR1245920A (fr) * 1960-01-19 1960-11-10 Le Ministre De La Defense Nati Collecteur de distribution de combustible isolé
GB938553A (en) * 1961-05-09 1963-10-02 Rolls Royce Reheat combustion apparatus for a gas turbine engine
FR1525092A (fr) * 1967-01-23 1968-05-17 Snecma Turbo-réacteur à flux de gaz chaud et à flux d'air froid
GB1211583A (en) * 1968-05-16 1970-11-11 Mini Of Technology Improvements in or relating to combustion devices
GB1255648A (en) * 1968-10-22 1971-12-01 Rolls Royce Duct burning system
US3646763A (en) * 1970-05-25 1972-03-07 Gen Electric Gas turbine engine with improved afterburner
US3698186A (en) * 1970-12-24 1972-10-17 United Aircraft Corp Afterburner combustion apparatus
FR2186608B1 (enrdf_load_stackoverflow) * 1972-04-17 1975-08-29 Snecma
US3765178A (en) * 1972-09-08 1973-10-16 Gen Electric Afterburner flameholder
FR2227436B1 (enrdf_load_stackoverflow) * 1973-04-27 1975-12-26 Snecma
US3931707A (en) * 1975-01-08 1976-01-13 General Electric Company Augmentor flameholding apparatus
FR2351258A1 (fr) * 1976-05-13 1977-12-09 Snecma Dispositif d'allumage de carburant injecte dans un milieu gazeux en ecoulement rapide
FR2404111A1 (fr) * 1977-09-27 1979-04-20 Snecma Dispositif de distribution de carburant

Also Published As

Publication number Publication date
EP0142389A1 (fr) 1985-05-22
US4592200A (en) 1986-06-03
JPH0366570B2 (enrdf_load_stackoverflow) 1991-10-17
FR2551500B1 (fr) 1985-11-08
DE3460874D1 (en) 1986-11-06
IL72744A0 (en) 1984-11-30
FR2551500A1 (fr) 1985-03-08
JPS60155827A (ja) 1985-08-15
IL72744A (en) 1992-03-29

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