FR3094777B1 - Chambre de combustion principale de turboréacteur équipée d’une grille en aval de ses bruleurs - Google Patents

Chambre de combustion principale de turboréacteur équipée d’une grille en aval de ses bruleurs Download PDF

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Publication number
FR3094777B1
FR3094777B1 FR1903588A FR1903588A FR3094777B1 FR 3094777 B1 FR3094777 B1 FR 3094777B1 FR 1903588 A FR1903588 A FR 1903588A FR 1903588 A FR1903588 A FR 1903588A FR 3094777 B1 FR3094777 B1 FR 3094777B1
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FR
France
Prior art keywords
combustion chamber
turbojet
burners
main combustion
chamber fitted
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.)
Active
Application number
FR1903588A
Other languages
English (en)
Other versions
FR3094777A1 (fr
Inventor
François Leglaye
Patrice André Commaret
Romain Nicolas Lunel
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
Safran Aircraft Engines SAS
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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1903588A priority Critical patent/FR3094777B1/fr
Publication of FR3094777A1 publication Critical patent/FR3094777A1/fr
Application granted granted Critical
Publication of FR3094777B1 publication Critical patent/FR3094777B1/fr
Active 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
    • F23R3/04—Air inlet arrangements
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • 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
    • F23R3/24—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants of the fluid-screen type
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L’invention concerne une chambre de combustion (26) de turbomachine, ayant une forme annulaire délimitée par un fond annulaire (27) prolongé par une virole radialement interne (28) et par une virole radialement externe (29). Selon l’invention, la chambre (26) est pourvue d’au moins un tube (34, 37, 38) alimenté en air qui la traverse, situé en aval du fond annulaire (27) et en ce que ce tube comporte des trous (36) d’injection d’air. Figure pour abrégé : Figure 5
FR1903588A 2019-04-04 2019-04-04 Chambre de combustion principale de turboréacteur équipée d’une grille en aval de ses bruleurs Active FR3094777B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1903588A FR3094777B1 (fr) 2019-04-04 2019-04-04 Chambre de combustion principale de turboréacteur équipée d’une grille en aval de ses bruleurs

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1903588 2019-04-04
FR1903588A FR3094777B1 (fr) 2019-04-04 2019-04-04 Chambre de combustion principale de turboréacteur équipée d’une grille en aval de ses bruleurs

Publications (2)

Publication Number Publication Date
FR3094777A1 FR3094777A1 (fr) 2020-10-09
FR3094777B1 true FR3094777B1 (fr) 2021-06-25

Family

ID=67262711

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1903588A Active FR3094777B1 (fr) 2019-04-04 2019-04-04 Chambre de combustion principale de turboréacteur équipée d’une grille en aval de ses bruleurs

Country Status (1)

Country Link
FR (1) FR3094777B1 (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3046731A (en) * 1955-10-07 1962-07-31 Edward Pohlmann Flame stabilization in jet engines
US5239818A (en) * 1992-03-30 1993-08-31 General Electric Company Dilution pole combustor and method
DE10214574A1 (de) * 2002-04-02 2003-10-16 Rolls Royce Deutschland Brennkammer für ein Luftstrahltriebwerk mit Sekundärluftzuführung
US7249461B2 (en) * 2003-08-22 2007-07-31 Siemens Power Generation, Inc. Turbine fuel ring assembly

Also Published As

Publication number Publication date
FR3094777A1 (fr) 2020-10-09

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