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FR3098569B1 - TURBOMACHINE COMBUSTION CHAMBER ANNULAR WALL INCLUDING PRIMARY HOLES, DILUTION HOLES AND INCLINED COOLING PORTS - Google Patents
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FR3098569B1 - TURBOMACHINE COMBUSTION CHAMBER ANNULAR WALL INCLUDING PRIMARY HOLES, DILUTION HOLES AND INCLINED COOLING PORTS - Google Patents

TURBOMACHINE COMBUSTION CHAMBER ANNULAR WALL INCLUDING PRIMARY HOLES, DILUTION HOLES AND INCLINED COOLING PORTS Download PDF

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Publication number
FR3098569B1
FR3098569B1 FR1907754A FR1907754A FR3098569B1 FR 3098569 B1 FR3098569 B1 FR 3098569B1 FR 1907754 A FR1907754 A FR 1907754A FR 1907754 A FR1907754 A FR 1907754A FR 3098569 B1 FR3098569 B1 FR 3098569B1
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FR
France
Prior art keywords
holes
combustion chamber
annular wall
annular surface
wall including
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
FR1907754A
Other languages
French (fr)
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FR3098569A1 (en
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
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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 FR1907754A priority Critical patent/FR3098569B1/en
Publication of FR3098569A1 publication Critical patent/FR3098569A1/en
Application granted granted Critical
Publication of FR3098569B1 publication Critical patent/FR3098569B1/en
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
    • F23R3/06—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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/03042—Film 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)

Abstract

L’invention concerne une paroi annulaire (11, 12) pour chambre de combustion de turbomachine, s’étendant autour d’un axe longitudinal (13) de direction axiale d’écoulement des gaz, la paroi annulaire présentant une surface annulaire chaude (18) opposée à une surface annulaire froide (20) et comprenant une pluralité de trous primaires (22) chacun centrés sur un premier axe (25), une pluralité de trous de dilution (23) situés en aval des trous primaires (22) dans la direction axiale d’écoulement des gaz et chacun centrés sur un deuxième axe (26), et une pluralité d’orifices de refroidissement (24) chacun centrés sur un troisième axe (27) incliné, d’amont en aval dans la direction axiale d’écoulement des gaz, de la surface annulaire froide à la surface annulaire chaude, les premiers axes et/ou les deuxièmes axes étant en outre chacun inclinés, d’amont en aval dans la direction axiale d’écoulement des gaz, de la surface annulaire froide à la surface annulaire chaude. Figure pour l’abrégé : Figure 6The invention relates to an annular wall (11, 12) for a turbomachine combustion chamber, extending around a longitudinal axis (13) in the axial direction of gas flow, the annular wall having a hot annular surface (18). ) opposite to a cold annular surface (20) and comprising a plurality of primary holes (22) each centered on a first axis (25), a plurality of dilution holes (23) located downstream of the primary holes (22) in the axial direction of gas flow and each centered on a second axis (26), and a plurality of cooling ports (24) each centered on a third axis (27) inclined, from upstream to downstream in the axial direction of gas flow from the cold annular surface to the hot annular surface, the first axes and / or the second axes each further being inclined, from upstream to downstream in the axial direction of gas flow, of the annular surface cold to the hot annular surface. Figure for the abstract: Figure 6

FR1907754A 2019-07-10 2019-07-10 TURBOMACHINE COMBUSTION CHAMBER ANNULAR WALL INCLUDING PRIMARY HOLES, DILUTION HOLES AND INCLINED COOLING PORTS Active FR3098569B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1907754A FR3098569B1 (en) 2019-07-10 2019-07-10 TURBOMACHINE COMBUSTION CHAMBER ANNULAR WALL INCLUDING PRIMARY HOLES, DILUTION HOLES AND INCLINED COOLING PORTS

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1907754 2019-07-10
FR1907754A FR3098569B1 (en) 2019-07-10 2019-07-10 TURBOMACHINE COMBUSTION CHAMBER ANNULAR WALL INCLUDING PRIMARY HOLES, DILUTION HOLES AND INCLINED COOLING PORTS

Publications (2)

Publication Number Publication Date
FR3098569A1 FR3098569A1 (en) 2021-01-15
FR3098569B1 true FR3098569B1 (en) 2021-07-16

Family

ID=67957159

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1907754A Active FR3098569B1 (en) 2019-07-10 2019-07-10 TURBOMACHINE COMBUSTION CHAMBER ANNULAR WALL INCLUDING PRIMARY HOLES, DILUTION HOLES AND INCLINED COOLING PORTS

Country Status (1)

Country Link
FR (1) FR3098569B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4202301B1 (en) * 2021-12-21 2026-03-11 General Electric Company Combustor with dilution openings

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2899315B1 (en) * 2006-03-30 2012-09-28 Snecma CONFIGURING DILUTION OPENINGS IN A TURBOMACHINE COMBUSTION CHAMBER WALL
FR2958012B1 (en) * 2010-03-23 2013-12-13 Snecma TURBOMACHINE COMBUSTION CHAMBER
DE102011114928A1 (en) * 2011-10-06 2013-04-11 Lufthansa Technik Ag Combustion chamber for a gas turbine
FR2982008B1 (en) 2011-10-26 2013-12-13 Snecma ANNULAR ROOM OF COMBUSTION CHAMBER WITH IMPROVED COOLING AT THE PRIMARY HOLES AND DILUTION HOLES
US10641490B2 (en) * 2017-01-04 2020-05-05 General Electric Company Combustor for use in a turbine engine
US11268438B2 (en) * 2017-09-15 2022-03-08 General Electric Company Combustor liner dilution opening

Also Published As

Publication number Publication date
FR3098569A1 (en) 2021-01-15

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