EP1818617A1 - Querwand einer Brennkammer, die mit Multiperforationslöchern ausgestattet ist - Google Patents

Querwand einer Brennkammer, die mit Multiperforationslöchern ausgestattet ist Download PDF

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Publication number
EP1818617A1
EP1818617A1 EP07101655A EP07101655A EP1818617A1 EP 1818617 A1 EP1818617 A1 EP 1818617A1 EP 07101655 A EP07101655 A EP 07101655A EP 07101655 A EP07101655 A EP 07101655A EP 1818617 A1 EP1818617 A1 EP 1818617A1
Authority
EP
European Patent Office
Prior art keywords
baffles
wall
turbomachine
combustion chamber
flow
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.)
Granted
Application number
EP07101655A
Other languages
English (en)
French (fr)
Other versions
EP1818617B1 (de
Inventor
Gérard CABOCHE
Claude Gautier
Denis Sandelis
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1818617A1 publication Critical patent/EP1818617A1/de
Application granted granted Critical
Publication of EP1818617B1 publication Critical patent/EP1818617B1/de
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
    • F23R3/10—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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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

Definitions

  • deflectors forming heat shields are also mounted in each opening of the chamber bottom around the injection systems. .
  • the chamber floor generally has a plurality of multiperforation holes that are drilled in the areas facing the baffles. These multiperforation holes are passages for air for impact cooling of the baffles.
  • the chamber bottom is in the form of a substantially plane ring which is centered on the longitudinal axis of the turbomachine. This may be either perpendicular to the longitudinal axis of the turbomachine, or inclined (inwardly or outwardly) relative to this axis.
  • each deflector comprises at least two deformations forming baffles for the flow of the cooling air flow, said deformations extending radially with respect to the longitudinal axis of the turbomachine from and other of the opening of the deflector.
  • FIG. 1 illustrates a combustion chamber for a turbomachine.
  • a turbomachine comprises in particular a compression section (not shown) in which air is compressed before being injected into a chamber housing 2, then into a combustion chamber 4 mounted inside thereof.
  • means are provided for forcing the flow of cooling air of the baffles 16 to flow radially around the fuel injection systems 14.
  • the deformations 20 are preferably formed in areas of the baffle which are not facing multiperforation holes.
  • the distance between the respective outer radial ends 10c, 16c of the transverse wall 10 and the deflectors 16 which is measured at the level of the radial plane of symmetry P of the deflectors is noted g .
  • the distance between the respective outer radial ends 10c, 16c of the transverse wall 10 and the deflectors 16 which is measured at the lateral ends of the baffles is denoted h .
  • each deflector 16 is arranged such that the distance g is smaller than the distance h . This can be obtained for example by bending the outer radial end 16c of the deflectors 16.

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)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Fuel-Injection Apparatus (AREA)
EP07101655A 2006-02-09 2007-02-02 Querwand einer Brennkammer, die mit Multiperforationslöchern ausgestattet ist Active EP1818617B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0650459A FR2897107B1 (fr) 2006-02-09 2006-02-09 Paroi transversale de chambre de combustion munie de trous de multiperforation

Publications (2)

Publication Number Publication Date
EP1818617A1 true EP1818617A1 (de) 2007-08-15
EP1818617B1 EP1818617B1 (de) 2012-08-29

Family

ID=37101624

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07101655A Active EP1818617B1 (de) 2006-02-09 2007-02-02 Querwand einer Brennkammer, die mit Multiperforationslöchern ausgestattet ist

Country Status (7)

Country Link
US (1) US7992391B2 (de)
EP (1) EP1818617B1 (de)
JP (1) JP2007211774A (de)
CN (1) CN101016999A (de)
CA (1) CA2577595C (de)
FR (1) FR2897107B1 (de)
RU (1) RU2426948C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3848634A1 (de) * 2020-01-07 2021-07-14 Raytheon Technologies Corporation Brennkammerdom mit kreisförmigem pralllochmuster

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2910115B1 (fr) * 2006-12-19 2012-11-16 Snecma Deflecteur pour fond de chambre de combustion, chambre de combustion en etant equipee et turboreacteur les comportant
FR2920525B1 (fr) * 2007-08-31 2014-06-13 Snecma Separateur pour alimentation de l'air de refroidissement d'une turbine
FR2932251B1 (fr) * 2008-06-10 2011-09-16 Snecma Chambre de combustion de moteur a turbine a gaz comportant des deflecteurs en cmc
US7712314B1 (en) 2009-01-21 2010-05-11 Gas Turbine Efficiency Sweden Ab Venturi cooling system
FR2958013B1 (fr) * 2010-03-26 2014-06-20 Snecma Chambre de combustion de turbomachine a compresseur centrifuge sans deflecteur
US9377198B2 (en) 2012-01-31 2016-06-28 United Technologies Corporation Heat shield for a combustor
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
US11313560B2 (en) 2018-07-18 2022-04-26 General Electric Company Combustor assembly for a heat engine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2637675A1 (fr) * 1988-10-12 1990-04-13 United Technologies Corp Chambre de combustion pour un turbomoteur
US5396759A (en) * 1990-08-16 1995-03-14 Rolls-Royce Plc Gas turbine engine combustor
US6164074A (en) * 1997-12-12 2000-12-26 United Technologies Corporation Combustor bulkhead with improved cooling and air recirculation zone
US20020178734A1 (en) * 2001-06-04 2002-12-05 Stastny Jan Honza Low cost combustor burner collar
US20040083735A1 (en) * 2002-11-05 2004-05-06 Honeywell International Inc. Gas turbine combustor heat shield impingement cooling baffle

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2410138A2 (fr) * 1977-11-29 1979-06-22 Snecma Perfectionnements aux chambres de combustion pour moteur a turbine a gaz
GB2247522B (en) * 1990-09-01 1993-11-10 Rolls Royce Plc Gas turbine engine combustor
US5419115A (en) * 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
DE4427222A1 (de) * 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
US5581999A (en) * 1994-12-15 1996-12-10 United Technologies Corporation Bulkhead liner with raised lip
US6155056A (en) * 1998-06-04 2000-12-05 Pratt & Whitney Canada Corp. Cooling louver for annular gas turbine engine combustion chamber
US6557349B1 (en) * 2000-04-17 2003-05-06 General Electric Company Method and apparatus for increasing heat transfer from combustors
US6530227B1 (en) * 2001-04-27 2003-03-11 General Electric Co. Methods and apparatus for cooling gas turbine engine combustors
US6546733B2 (en) * 2001-06-28 2003-04-15 General Electric Company Methods and systems for cooling gas turbine engine combustors
FR2836986B1 (fr) * 2002-03-07 2004-11-19 Snecma Moteurs Systeme d'injection multi-modes d'un melange air/carburant dans une chambre de combustion
US8596071B2 (en) * 2006-05-05 2013-12-03 General Electric Company Method and apparatus for assembling a gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2637675A1 (fr) * 1988-10-12 1990-04-13 United Technologies Corp Chambre de combustion pour un turbomoteur
US5396759A (en) * 1990-08-16 1995-03-14 Rolls-Royce Plc Gas turbine engine combustor
US6164074A (en) * 1997-12-12 2000-12-26 United Technologies Corporation Combustor bulkhead with improved cooling and air recirculation zone
US20020178734A1 (en) * 2001-06-04 2002-12-05 Stastny Jan Honza Low cost combustor burner collar
US20040083735A1 (en) * 2002-11-05 2004-05-06 Honeywell International Inc. Gas turbine combustor heat shield impingement cooling baffle

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3848634A1 (de) * 2020-01-07 2021-07-14 Raytheon Technologies Corporation Brennkammerdom mit kreisförmigem pralllochmuster

Also Published As

Publication number Publication date
JP2007211774A (ja) 2007-08-23
US7992391B2 (en) 2011-08-09
RU2426948C2 (ru) 2011-08-20
CN101016999A (zh) 2007-08-15
FR2897107A1 (fr) 2007-08-10
CA2577595A1 (fr) 2007-08-09
US20070180834A1 (en) 2007-08-09
EP1818617B1 (de) 2012-08-29
CA2577595C (fr) 2014-12-23
RU2007104918A (ru) 2008-08-20
FR2897107B1 (fr) 2013-01-18

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