FR3132562B1 - Chambre de combustion d’une turbomachine - Google Patents

Chambre de combustion d’une turbomachine

Info

Publication number
FR3132562B1
FR3132562B1 FR2201158A FR2201158A FR3132562B1 FR 3132562 B1 FR3132562 B1 FR 3132562B1 FR 2201158 A FR2201158 A FR 2201158A FR 2201158 A FR2201158 A FR 2201158A FR 3132562 B1 FR3132562 B1 FR 3132562B1
Authority
FR
France
Prior art keywords
annular part
combustion chamber
turbomachine
casing
tubular
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
FR2201158A
Other languages
English (en)
Other versions
FR3132562A1 (fr
Inventor
Romain Nicolas Lunel
Damien Bonnefoi
Arnaud Bernard Clément Thomas Joudareff
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 FR2201158A priority Critical patent/FR3132562B1/fr
Publication of FR3132562A1 publication Critical patent/FR3132562A1/fr
Application granted granted Critical
Publication of FR3132562B1 publication Critical patent/FR3132562B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • F02C7/266—Electric
    • 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
    • F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses
    • 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
    • F23R2900/00012—Details of sealing devices
    • 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)
  • Vibration Prevention Devices (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)

Abstract

Ensemble de chambre de combustion (10) d’une turbomachine d’aéronef comportant un carter (11), et un dispositif tubulaire de fixation (23) d’une bougie d’allumage (22) sur le carter (11), le dispositif tubulaire de fixation (23) comprenant :- une première partie annulaire (24) dans laquelle la bougie d’allumage (22) est apte à être montée à étanchéité,- et une seconde partie annulaire (25) fixée à étanchéité sur le carter (11),le dispositif tubulaire de fixation (23) comprenant en outre un moyen amortisseur de vibration (30) reliant la première partie annulaire (24) à la seconde partie annulaire (25). Figure de l’abrégé : Figure 3
FR2201158A 2022-02-10 2022-02-10 Chambre de combustion d’une turbomachine Active FR3132562B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2201158A FR3132562B1 (fr) 2022-02-10 2022-02-10 Chambre de combustion d’une turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2201158 2022-02-10
FR2201158A FR3132562B1 (fr) 2022-02-10 2022-02-10 Chambre de combustion d’une turbomachine

Related Child Applications (1)

Application Number Title Priority Date Filing Date
FR2508631A Division FR3165057A1 (fr) 2025-07-25 2025-07-25 Chambre de combustion d’une turbomachine

Publications (2)

Publication Number Publication Date
FR3132562A1 FR3132562A1 (fr) 2023-08-11
FR3132562B1 true FR3132562B1 (fr) 2025-08-29

Family

ID=82319715

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2201158A Active FR3132562B1 (fr) 2022-02-10 2022-02-10 Chambre de combustion d’une turbomachine

Country Status (1)

Country Link
FR (1) FR3132562B1 (fr)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3793838A (en) * 1972-09-05 1974-02-26 Gen Electric Augmenter fuel injection mounting system
US3990834A (en) * 1973-09-17 1976-11-09 General Electric Company Cooled igniter
DE4320428A1 (de) * 1993-06-21 1994-12-22 Abb Management Ag Sondendurchführung für eine Brennkammer
DE4340616A1 (de) * 1993-11-29 1995-06-01 Bmw Rolls Royce Gmbh Befestigungsanordnung einer Zündkerze einer Gasturbine
US20100212324A1 (en) * 2009-02-26 2010-08-26 Honeywell International Inc. Dual walled combustors with impingement cooled igniters
FR3015642B1 (fr) * 2013-12-23 2018-03-02 Safran Aircraft Engines Bougie de turbomachine et son dispositif de fixation radiale
US10465610B2 (en) * 2017-03-03 2019-11-05 General Electric Company Sealing assembly for components penetrating through CMC liner
FR3072422B1 (fr) * 2017-10-17 2020-10-02 Safran Aircraft Engines Module de chambre de combustion pour une turbomachine

Also Published As

Publication number Publication date
FR3132562A1 (fr) 2023-08-11

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