FR2975465B1 - WALL FOR TURBOMACHINE COMBUSTION CHAMBER COMPRISING AN OPTIMIZED AIR INLET ORIFICE ARRANGEMENT - Google Patents

WALL FOR TURBOMACHINE COMBUSTION CHAMBER COMPRISING AN OPTIMIZED AIR INLET ORIFICE ARRANGEMENT Download PDF

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Publication number
FR2975465B1
FR2975465B1 FR1154387A FR1154387A FR2975465B1 FR 2975465 B1 FR2975465 B1 FR 2975465B1 FR 1154387 A FR1154387 A FR 1154387A FR 1154387 A FR1154387 A FR 1154387A FR 2975465 B1 FR2975465 B1 FR 2975465B1
Authority
FR
France
Prior art keywords
wall
air inlet
combustion chamber
inlet orifice
orifice arrangement
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
FR1154387A
Other languages
French (fr)
Other versions
FR2975465A1 (en
Inventor
Andre Commaret Patrice
Marcel Arthur Bunel Jacques
Hippolyte Hernandez Didier
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
SNECMA 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, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1154387A priority Critical patent/FR2975465B1/en
Priority to US13/475,306 priority patent/US20120291442A1/en
Publication of FR2975465A1 publication Critical patent/FR2975465A1/en
Application granted granted Critical
Publication of FR2975465B1 publication Critical patent/FR2975465B1/en
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
    • F23R3/02—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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
FR1154387A 2011-05-19 2011-05-19 WALL FOR TURBOMACHINE COMBUSTION CHAMBER COMPRISING AN OPTIMIZED AIR INLET ORIFICE ARRANGEMENT Active FR2975465B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1154387A FR2975465B1 (en) 2011-05-19 2011-05-19 WALL FOR TURBOMACHINE COMBUSTION CHAMBER COMPRISING AN OPTIMIZED AIR INLET ORIFICE ARRANGEMENT
US13/475,306 US20120291442A1 (en) 2011-05-19 2012-05-18 Wall for a turbomachine combustion chamber including an optimised arrangement of air inlet apertures

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1154387A FR2975465B1 (en) 2011-05-19 2011-05-19 WALL FOR TURBOMACHINE COMBUSTION CHAMBER COMPRISING AN OPTIMIZED AIR INLET ORIFICE ARRANGEMENT
FR1154387 2011-05-19

Publications (2)

Publication Number Publication Date
FR2975465A1 FR2975465A1 (en) 2012-11-23
FR2975465B1 true FR2975465B1 (en) 2018-03-09

Family

ID=44549672

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1154387A Active FR2975465B1 (en) 2011-05-19 2011-05-19 WALL FOR TURBOMACHINE COMBUSTION CHAMBER COMPRISING AN OPTIMIZED AIR INLET ORIFICE ARRANGEMENT

Country Status (2)

Country Link
US (1) US20120291442A1 (en)
FR (1) FR2975465B1 (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2964725B1 (en) 2010-09-14 2012-10-12 Snecma AERODYNAMIC FAIRING FOR BOTTOM OF COMBUSTION CHAMBER
US9217568B2 (en) * 2012-06-07 2015-12-22 United Technologies Corporation Combustor liner with decreased liner cooling
US9335049B2 (en) * 2012-06-07 2016-05-10 United Technologies Corporation Combustor liner with reduced cooling dilution openings
FR3009747B1 (en) * 2013-08-19 2018-06-15 Snecma TURBOMACHINE COMBUSTION CHAMBER WITH IMPROVED AIR INPUT PASSING DOWN A CANDLE PITCH ORIFICE
FR3011620B1 (en) * 2013-10-04 2018-03-09 Snecma TURBOMACHINE COMBUSTION CHAMBER WITH IMPROVED AIR INPUT PASSING DOWN A CANDLE PITCH ORIFICE
EP3018415B1 (en) * 2014-11-07 2020-01-01 United Technologies Corporation Combustor dilution hole cooling
US10670267B2 (en) * 2015-08-14 2020-06-02 Raytheon Technologies Corporation Combustor hole arrangement for gas turbine engine
US10816202B2 (en) * 2017-11-28 2020-10-27 General Electric Company Combustor liner for a gas turbine engine and an associated method thereof
US11255543B2 (en) 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
FR3095260B1 (en) * 2019-04-18 2021-03-19 Safran Aircraft Engines PROCESS FOR DEFINING HOLES FOR PASSING AIR THROUGH A COMBUSTION CHAMBER WALL

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB594285A (en) * 1944-03-16 1947-11-07 Power Jets Ltd Improvements relating to combustion apparatus
US5289686A (en) * 1992-11-12 1994-03-01 General Motors Corporation Low nox gas turbine combustor liner with elliptical apertures for air swirling
FR2892180B1 (en) * 2005-10-18 2008-02-01 Snecma Sa IMPROVING THE PERFOMANCE OF A COMBUSTION CHAMBER BY MULTIPERFORATING THE WALLS
US8028529B2 (en) * 2006-05-04 2011-10-04 General Electric Company Low emissions gas turbine combustor
US7905094B2 (en) * 2007-09-28 2011-03-15 Honeywell International Inc. Combustor systems with liners having improved cooling hole patterns
FR2950415B1 (en) * 2009-09-21 2011-10-14 Snecma COMBUSTION CHAMBER FOR AERONAUTICAL TURBOMACHINE WITH DECAL COMBUSTION HOLES OR DIFFERENT RATES

Also Published As

Publication number Publication date
US20120291442A1 (en) 2012-11-22
FR2975465A1 (en) 2012-11-23

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