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FR3095260B1 - Procede de definition de trous de passage d’air a travers une paroi de chambre de combustion - Google Patents

Procede de definition de trous de passage d’air a travers une paroi de chambre de combustion Download PDF

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Publication number
FR3095260B1
FR3095260B1 FR1904171A FR1904171A FR3095260B1 FR 3095260 B1 FR3095260 B1 FR 3095260B1 FR 1904171 A FR1904171 A FR 1904171A FR 1904171 A FR1904171 A FR 1904171A FR 3095260 B1 FR3095260 B1 FR 3095260B1
Authority
FR
France
Prior art keywords
multiperforations
combustion chamber
virtually
hole
chamber wall
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 - Fee Related
Application number
FR1904171A
Other languages
English (en)
Other versions
FR3095260A1 (fr
Inventor
François Pierre Georges Maurice Ribassin
Patrice André Commaret
Romain Nicolas Lunel
Christophe Pieussergues
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 FR1904171A priority Critical patent/FR3095260B1/fr
Priority to CN202010293679.3A priority patent/CN111829006B/zh
Priority to US16/850,114 priority patent/US11441779B2/en
Priority to EP20170100.0A priority patent/EP3734162B1/fr
Publication of FR3095260A1 publication Critical patent/FR3095260A1/fr
Application granted granted Critical
Publication of FR3095260B1 publication Critical patent/FR3095260B1/fr
Expired - Fee Related 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • 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
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Respiratory Apparatuses And Protective Means (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L’invention concerne la mise en place de trous (25,27) de passage d’air à travers une paroi (3,5) de chambre de combustion de turbomachine à gaz. On positionne virtuellement des multiperforations que l’on répartit, y compris dans une première zone de sécurité sans orifice de passage d’air. On enlève virtuellement les multiperforations dont une entrée ou sortie virtuelle se situe dans cette première zone de sécurité. En fonction de certains critères, on réintègre ensuite virtuellement certains au moins desdites multiperforations enlevées, et, depuis alors un périmètre passant par les entrées et sorties virtuelles de l’ensemble des multiperforations présentes, on définit, en direction d’un trou primaire ou de dilution à installer, une zone de sécurité modifiée, puis, en respectant autour dudit trou et avec la liberté de le repositionner dans cette limite, on redéfinit la forme de ce trou. Figure à publier avec l’abrégé : Figure 1
FR1904171A 2019-04-18 2019-04-18 Procede de definition de trous de passage d’air a travers une paroi de chambre de combustion Expired - Fee Related FR3095260B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FR1904171A FR3095260B1 (fr) 2019-04-18 2019-04-18 Procede de definition de trous de passage d’air a travers une paroi de chambre de combustion
CN202010293679.3A CN111829006B (zh) 2019-04-18 2020-04-15 在燃烧室壁中构造和定位通气孔
US16/850,114 US11441779B2 (en) 2019-04-18 2020-04-16 Configuring and positioning air passage holes in a combustion chamber wall
EP20170100.0A EP3734162B1 (fr) 2019-04-18 2020-04-17 Procédé de définition de trous de passage d air à travers une paroi de chambre de combustion

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1904171A FR3095260B1 (fr) 2019-04-18 2019-04-18 Procede de definition de trous de passage d’air a travers une paroi de chambre de combustion
FR1904171 2019-04-18

Publications (2)

Publication Number Publication Date
FR3095260A1 FR3095260A1 (fr) 2020-10-23
FR3095260B1 true FR3095260B1 (fr) 2021-03-19

Family

ID=67185501

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1904171A Expired - Fee Related FR3095260B1 (fr) 2019-04-18 2019-04-18 Procede de definition de trous de passage d’air a travers une paroi de chambre de combustion

Country Status (4)

Country Link
US (1) US11441779B2 (fr)
EP (1) EP3734162B1 (fr)
CN (1) CN111829006B (fr)
FR (1) FR3095260B1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12247738B2 (en) * 2020-01-17 2025-03-11 Rtx Corporation Convection cooling at low effusion density region of combustor panel
US11920790B2 (en) * 2021-11-03 2024-03-05 General Electric Company Wavy annular dilution slots for lower emissions
US12007114B1 (en) 2023-03-21 2024-06-11 General Electric Company Gas turbine engine combustor with openings

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7036316B2 (en) * 2003-10-17 2006-05-02 General Electric Company Methods and apparatus for cooling turbine engine combustor exit temperatures
FR2881813B1 (fr) * 2005-02-09 2011-04-08 Snecma Moteurs Carenage de chambre de combustion de turbomachine
FR2899315B1 (fr) * 2006-03-30 2012-09-28 Snecma Configuration d'ouvertures de dilution dans une paroi de chambre de combustion de turbomachine
FR2922630B1 (fr) * 2007-10-22 2015-11-13 Snecma Paroi de chambre de combustion a dilution et refroidissement optimises,chambre de combustion et turbomachine en etant munies
US20100257863A1 (en) * 2009-04-13 2010-10-14 General Electric Company Combined convection/effusion cooled one-piece can combustor
JP5075900B2 (ja) * 2009-09-30 2012-11-21 株式会社日立製作所 水素含有燃料対応燃焼器および、その低ＮＯｘ運転方法
FR2970666B1 (fr) * 2011-01-24 2013-01-18 Snecma Procede de perforation d'au moins une paroi d'une chambre de combustion
FR2975465B1 (fr) * 2011-05-19 2018-03-09 Safran Aircraft Engines Paroi pour chambre de combustion de turbomachine comprenant un agencement optimise d'orifices d'entree d'air
EP3066387B1 (fr) * 2013-11-04 2019-10-02 United Technologies Corporation Ensemble pour moteur de turbine comprenant une chambre de combustion avec ouvertures d'air de dilution
FR3037107B1 (fr) * 2015-06-03 2019-11-15 Safran Aircraft Engines Paroi annulaire de chambre de combustion a refroidissement optimise

Also Published As

Publication number Publication date
US11441779B2 (en) 2022-09-13
US20200333008A1 (en) 2020-10-22
CN111829006B (zh) 2023-01-10
CN111829006A (zh) 2020-10-27
EP3734162B1 (fr) 2022-03-02
EP3734162A1 (fr) 2020-11-04
FR3095260A1 (fr) 2020-10-23

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