FR3114636B1 - Chambre de combustion pour une turbomachine - Google Patents

Chambre de combustion pour une turbomachine Download PDF

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Publication number
FR3114636B1
FR3114636B1 FR2009983A FR2009983A FR3114636B1 FR 3114636 B1 FR3114636 B1 FR 3114636B1 FR 2009983 A FR2009983 A FR 2009983A FR 2009983 A FR2009983 A FR 2009983A FR 3114636 B1 FR3114636 B1 FR 3114636B1
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FR
France
Prior art keywords
combustion chamber
radially
internal
distributor
extending
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
FR2009983A
Other languages
English (en)
Other versions
FR3114636A1 (fr
Inventor
François Xavier Chapelle
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 FR2009983A priority Critical patent/FR3114636B1/fr
Publication of FR3114636A1 publication Critical patent/FR3114636A1/fr
Application granted granted Critical
Publication of FR3114636B1 publication Critical patent/FR3114636B1/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
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’invention concerne une turbomachine s’étendant selon un axe, comportant une chambre de combustion (1) et un distributeur (14) de turbine situé en aval de la chambre de combustion (1), la chambre de combustion (1) comportant une paroi annulaire radialement externe (3) et une paroi annulaire radialement interne (2) coaxiales et délimitant entre elles un volume interne (7), le distributeur (14) comportant une virole radialement interne (15) et une virole radialement externe (16) s’étendant respectivement dans le prolongement des parois radialement interne (2) et externe (3) de la chambre de combustion (1) et reliées par des pales (17) s’étendant radialement, chaque pale (17) comportant un bord d’attaque amont (30), l’extrémité aval d’au moins une paroi (2, 3) étant prolongée par un rebord annulaire radial (18) s’étendant à l’opposé du volume interne (7) de la chambre (1) et délimitant un espace annulaire (20) avec la virole correspondante (15, 16) du distributeur (14). Figure à publier avec l’abrégé : Figure numéro 1 [Fig. 1]
FR2009983A 2020-09-30 2020-09-30 Chambre de combustion pour une turbomachine Active FR3114636B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2009983A FR3114636B1 (fr) 2020-09-30 2020-09-30 Chambre de combustion pour une turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2009983A FR3114636B1 (fr) 2020-09-30 2020-09-30 Chambre de combustion pour une turbomachine
FR2009983 2020-09-30

Publications (2)

Publication Number Publication Date
FR3114636A1 FR3114636A1 (fr) 2022-04-01
FR3114636B1 true FR3114636B1 (fr) 2023-10-27

Family

ID=74347204

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2009983A Active FR3114636B1 (fr) 2020-09-30 2020-09-30 Chambre de combustion pour une turbomachine

Country Status (1)

Country Link
FR (1) FR3114636B1 (fr)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9305010D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc A cooled turbine nozzle assembly and a method of calculating the diameters of cooling holes for use in such an assembly
GB9304994D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc Improvements in or relating to gas turbine engines
FR2921463B1 (fr) 2007-09-26 2013-12-06 Snecma Chambre de combustion d'une turbomachine
FR2937098B1 (fr) * 2008-10-15 2015-11-20 Snecma Etancheite entre une chambre de combustion et un distributeur de turbine dans une turbomachine
US8707705B2 (en) * 2009-09-03 2014-04-29 General Electric Company Impingement cooled transition piece aft frame
US10584601B2 (en) * 2017-08-30 2020-03-10 United Technologies Corporation Conformal seal and vane bow wave cooling

Also Published As

Publication number Publication date
FR3114636A1 (fr) 2022-04-01

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