EP2275743A3 - Gas turbine combustion chamber with starter film for cooling the combustion chamber wall - Google Patents

Gas turbine combustion chamber with starter film for cooling the combustion chamber wall Download PDF

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Publication number
EP2275743A3
EP2275743A3 EP10005467.5A EP10005467A EP2275743A3 EP 2275743 A3 EP2275743 A3 EP 2275743A3 EP 10005467 A EP10005467 A EP 10005467A EP 2275743 A3 EP2275743 A3 EP 2275743A3
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
cooling
gas turbine
chamber wall
starter film
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.)
Withdrawn
Application number
EP10005467.5A
Other languages
German (de)
French (fr)
Other versions
EP2275743A2 (en
Inventor
Miklos Dr. Gerendas
Sermed Sadig
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2275743A2 publication Critical patent/EP2275743A2/en
Publication of EP2275743A3 publication Critical patent/EP2275743A3/en
Withdrawn legal-status Critical Current

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
    • 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

Die Erfindung bezieht sich auf eine Gasturbinenbrennkammer mit Starterfilm zur Kühlung der Brennkammerwand, mit einem durch ein Hitzeschild (5) zur Brennkammer hin begrenzten Brennkammerkopf, in welchen Kühlluft einleitbar ist, wobei beabstandet zu dem Hitzeschild (5) eine Grundplatte (2) angeordnet ist, welche an ihrem Randbereich mit mehreren Öffnungen (6) zur Durchführung von Kühlluft versehen ist, dadurch gekennzeichnet, dass die Mittelachsen (17) der Öffnungen (6) in einem flachen Winkel (α) zur Brennkammerwand (4) geneigt ausgebildet sind.

Figure imgaf001
The invention relates to a gas turbine combustion chamber with a starter film for cooling the combustion chamber wall, with a combustion chamber head delimited by a heat shield (5) towards the combustion chamber, in which cooling air can be introduced, wherein a base plate (2) is arranged at a distance from the heat shield (5). which is provided at its edge region with a plurality of openings (6) for the passage of cooling air, characterized in that the central axes (17) of the openings (6) at an angle (α) to the combustion chamber wall (4) are inclined.
Figure imgaf001
EP10005467.5A 2009-07-17 2010-05-26 Gas turbine combustion chamber with starter film for cooling the combustion chamber wall Withdrawn EP2275743A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009033592A DE102009033592A1 (en) 2009-07-17 2009-07-17 Gas turbine combustion chamber with starter film for cooling the combustion chamber wall

Publications (2)

Publication Number Publication Date
EP2275743A2 EP2275743A2 (en) 2011-01-19
EP2275743A3 true EP2275743A3 (en) 2017-12-06

Family

ID=42983670

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10005467.5A Withdrawn EP2275743A3 (en) 2009-07-17 2010-05-26 Gas turbine combustion chamber with starter film for cooling the combustion chamber wall

Country Status (3)

Country Link
US (1) US8938970B2 (en)
EP (1) EP2275743A3 (en)
DE (1) DE102009033592A1 (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9057523B2 (en) * 2011-07-29 2015-06-16 United Technologies Corporation Microcircuit cooling for gas turbine engine combustor
US9335049B2 (en) 2012-06-07 2016-05-10 United Technologies Corporation Combustor liner with reduced cooling dilution openings
US9243801B2 (en) 2012-06-07 2016-01-26 United Technologies Corporation Combustor liner with improved film cooling
US9239165B2 (en) 2012-06-07 2016-01-19 United Technologies Corporation Combustor liner with convergent cooling channel
US9217568B2 (en) 2012-06-07 2015-12-22 United Technologies Corporation Combustor liner with decreased liner cooling
US9599343B2 (en) * 2012-11-28 2017-03-21 General Electric Company Fuel nozzle for use in a turbine engine and method of assembly
EP2886798B1 (en) 2013-12-20 2018-10-24 Rolls-Royce Corporation mechanically machined film cooling holes
US10267521B2 (en) 2015-04-13 2019-04-23 Pratt & Whitney Canada Corp. Combustor heat shield
US10473332B2 (en) * 2016-02-25 2019-11-12 General Electric Company Combustor assembly
GB201715366D0 (en) 2017-09-22 2017-11-08 Rolls Royce Plc A combustion chamber
US11092076B2 (en) 2017-11-28 2021-08-17 General Electric Company Turbine engine with combustor
DE102018212394B4 (en) 2018-07-25 2024-03-28 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with a wall element having a flow guide device
US11293638B2 (en) * 2019-08-23 2022-04-05 Raytheon Technologies Corporation Combustor heat shield and method of cooling same
US11525577B2 (en) 2020-04-27 2022-12-13 Raytheon Technologies Corporation Extended bulkhead panel

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5307637A (en) * 1992-07-09 1994-05-03 General Electric Company Angled multi-hole film cooled single wall combustor dome plate
US5329761A (en) * 1991-07-01 1994-07-19 General Electric Company Combustor dome assembly
US5353587A (en) * 1992-06-12 1994-10-11 General Electric Company Film cooling starter geometry for combustor lines
DE4427222A1 (en) * 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Heat shield for a gas turbine combustor
US20040083735A1 (en) * 2002-11-05 2004-05-06 Honeywell International Inc. Gas turbine combustor heat shield impingement cooling baffle
US20080104962A1 (en) * 2006-11-03 2008-05-08 Patel Bhawan B Combustor dome panel heat shield cooling

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3420058A (en) 1967-01-03 1969-01-07 Gen Electric Combustor liners
US4566280A (en) 1983-03-23 1986-01-28 Burr Donald N Gas turbine engine combustor splash ring construction
GB2150277B (en) * 1983-11-26 1987-01-28 Rolls Royce Combustion apparatus for a gas turbine engine
US4651534A (en) * 1984-11-13 1987-03-24 Kongsberg Vapenfabrikk Gas turbine engine combustor
JP2928607B2 (en) 1989-12-22 1999-08-03 株式会社日立製作所 Combustion apparatus and combustion method thereof
US5181379A (en) 1990-11-15 1993-01-26 General Electric Company Gas turbine engine multi-hole film cooled combustor liner and method of manufacture
CA2056592A1 (en) 1990-12-21 1992-06-22 Phillip D. Napoli Multi-hole film cooled combustor liner with slotted film starter
US5142871A (en) * 1991-01-22 1992-09-01 General Electric Company Combustor dome plate support having uniform thickness arcuate apex with circumferentially spaced coolant apertures
US5435139A (en) 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
DE19508111A1 (en) 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Heat shield arrangement for a gas turbine combustor
FR2753779B1 (en) * 1996-09-26 1998-10-16 AERODYNAMIC INJECTION SYSTEM FOR A FUEL AIR MIXTURE
US6266961B1 (en) * 1999-10-14 2001-07-31 General Electric Company Film cooled combustor liner and method of making the same
GB9926257D0 (en) 1999-11-06 2000-01-12 Rolls Royce Plc Wall elements for gas turbine engine combustors
US6546732B1 (en) * 2001-04-27 2003-04-15 General Electric Company 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
DE10214573A1 (en) 2002-04-02 2003-10-16 Rolls Royce Deutschland Combustion chamber of a gas turbine with starter film cooling
US6955053B1 (en) * 2002-07-01 2005-10-18 Hamilton Sundstrand Corporation Pyrospin combuster
US7308794B2 (en) * 2004-08-27 2007-12-18 Pratt & Whitney Canada Corp. Combustor and method of improving manufacturing accuracy thereof
US7260936B2 (en) * 2004-08-27 2007-08-28 Pratt & Whitney Canada Corp. Combustor having means for directing air into the combustion chamber in a spiral pattern
US7614235B2 (en) * 2005-03-01 2009-11-10 United Technologies Corporation Combustor cooling hole pattern

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5329761A (en) * 1991-07-01 1994-07-19 General Electric Company Combustor dome assembly
US5353587A (en) * 1992-06-12 1994-10-11 General Electric Company Film cooling starter geometry for combustor lines
US5307637A (en) * 1992-07-09 1994-05-03 General Electric Company Angled multi-hole film cooled single wall combustor dome plate
DE4427222A1 (en) * 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Heat shield for a gas turbine combustor
US20040083735A1 (en) * 2002-11-05 2004-05-06 Honeywell International Inc. Gas turbine combustor heat shield impingement cooling baffle
US20080104962A1 (en) * 2006-11-03 2008-05-08 Patel Bhawan B Combustor dome panel heat shield cooling

Also Published As

Publication number Publication date
US8938970B2 (en) 2015-01-27
DE102009033592A1 (en) 2011-01-20
EP2275743A2 (en) 2011-01-19
US20110011093A1 (en) 2011-01-20

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