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EP0576435B1 - Gasturbinenbrennkammer - Google Patents

Gasturbinenbrennkammer Download PDF

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Publication number
EP0576435B1
EP0576435B1 EP92904247A EP92904247A EP0576435B1 EP 0576435 B1 EP0576435 B1 EP 0576435B1 EP 92904247 A EP92904247 A EP 92904247A EP 92904247 A EP92904247 A EP 92904247A EP 0576435 B1 EP0576435 B1 EP 0576435B1
Authority
EP
European Patent Office
Prior art keywords
wall
gas turbine
wall elements
turbine engine
elements
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 - Lifetime
Application number
EP92904247A
Other languages
English (en)
French (fr)
Other versions
EP0576435A1 (de
Inventor
Anthony Pidcock
Stephen Mark Cooper
Peter Fry
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 PLC
Original Assignee
Rolls Royce PLC
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
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=10692006&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP0576435(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP0576435A1 publication Critical patent/EP0576435A1/de
Application granted granted Critical
Publication of EP0576435B1 publication Critical patent/EP0576435B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/202—Heat transfer, e.g. cooling by film cooling
    • 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

  • This invention relates to a gas turbine engine combustor and in particular to the construction of the wall of such a combustor.
  • the combustion process which takes place within the combustor of a gas turbine engine results in the combustor walls being exposed to extremely high temperatures.
  • the alloys used in combustor wall construction are normally unable to withstand these temperatures without some form of cooling.
  • Various combustor wall designs have been employed in the past which make use of pressurised air derived from the engine compressor for cooling purposes.
  • the wall is made up of two parts: a continuous outer wall and an inner wall made up of a number of partially overlapping inner wall elements.
  • the outer wall and inner wall elements are maintained in spaced apart relationship and cooling air is directed through holes in the outer wall into the space defined between them.
  • the cooling air flows through the space to be exhausted through gaps defined between the overlapping portions of the inner wall elements.
  • the cooling air thereby provides convection cooling as it flows between the inner wall elements and outer wall and film cooling of the inner wall elements after it has been exhausted from the gaps between inner wall elements.
  • a gas turbine engine annular combustor has a radially inner wall structure and a radially outer wall structure, each wall structure compring a radially outer wall and a radially inner wall, said radially inner wall being constituted by a plurality of discreet wall elements, means being provided to maintain said wall elements and said radially outer wall in spaced apart relationship, said radially outer wall being apertured to permit the flow of cooling fluid into the spaces defined between said radially outer wall and said wall elements, each of said wall elements being apertured to facilitate the exhaustion of said cooling fluid from said spaces, means being provided to interconnect the periphery of each wall element and said outer wall said interconnection means defining a continuous wall around each wall element periphery which is integral with that periphery so that a discreet chamber is thereby defined between each of said wall elements and said radially outer wall for the flow therethrough of said cooling fluid.
  • a ducted fan gas turbine engine generally indicated at 10 comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, combustion equipment 15, a high pressure turbine 16, an intermediate pressure turbine 17, a low pressure turbine 18 and an exhaust nozzle 19.
  • the gas turbine engine 10 works in the conventional manner so that air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow into the intermediate pressure compressor 13 and a second airflow which provides propulsive thrust.
  • the intermediate pressure compressor 13 compresses the air flow directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
  • the compressed air exhausted from the high pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines 16,17 and 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust.
  • the high, intermediate and low pressure turbines 16,17 and 18 respectively drive the high and intermediate pressure compressors 14 and 13 and the fan 12 by suitable interconnecting shafts.
  • the combustion equipment 15 is constituted by an annular combustor 20 having radially inner and outer wall structures 21 and 22 respectively. Fuel is directed into the combustor 20 through a number of fuel nozzles (-not shown) located at the upstream end 23 of the combustor 20. The fuel nozzles are circumferentially spaced around the engine 10 and serve to spray fuel into air derived from the high pressure compressor 14. The resultant fuel/air mixture is them combusted within the combustor 20.
  • the radially outer wall structure 22 can be seen more clearly if reference is now made to figure 2. It will be appreciated, however, that the radially inner wall structure 21 is of the same general configuration as the radially outer wall structure 22.
  • the radially outer wall structure 22 comprises an outer wall 24 and an inner wall 25.
  • the inner wall 25 is made up of a plurality of discreet wall elements 26 which are all of the same general rectangular configuration and are positioned adjacent each other. The majority of each wall element 26 is arranged to be equi-distant from the outer wall 24. However, the periphery of each wall element 26 is provided with a continuous flange 27 to facilitate the spacing apart of the wall element 26 and the outer wall 24. It will be seen therefore that a chamber 28 is thereby defined between each wall element 26 and the outer wall 24.
  • Each wall element 26 is of cast construction and is provided with integral bolts 29 which facilitate its attachment to the outer wall 24.
  • the angled effusion holes 32 which can be seen more clearly in figures 4 and 5, are not of circular cross-sectional shape. Instead they are all of the so-called race-track configuration, that is, they have two parallel sides interconnected by semi-circular cross-section portions. This shape, together with the inclination of the hole 32, ensures that air exhausted from them forms a film of cooling air over the inward surface of each wall element 26, that is, the surface which confronts the combustion process which takes place within the combustor 20. This film of cooling air assists in protecting the wall elements 26 from the effects of the high temperature gases within the combustor 20.
  • each of the wall elements 26 is provided with two highly effective forms of cooling: impingement cooling and film cooling. They are therefore fully protected from the effects of the high temperatures within the combustor 20.
  • a further feature of the present invention is that none of the wall elements 26 presents exposed edges to the combustion process within the combustor 20. Consequently the overheating problems which may be experienced with wall elements having such exposed edges are avoided.
  • pedestals 33 are integral with the wall elements 26 and engage or terminate very close to the outer wall 24.
  • the provision of the pedestals 33, which tend to be located in the central region of each wall element 26, results in a reduction in the number of the angled effusion holes 32 in each wall element 26. Consequently, the angled effusion holes 32 tend to be concentrated in the edge regions of the wall elements 26.

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)

Claims (10)

  1. Ringbrennkammer (15) für ein Gasturbinentriebwerk mit einem radial inneren Wandaufbau (21) und einem radial äußeren Wandaufbau (22), wobei jeder Wandaufbau eine radial äußere Wand (24) und eine radial innere Wand (25) besitzt und die radial innere Wand (25) aus mehreren einzelnen Wandelementen (26) besteht, und wobei Mittel vorgesehen sind, um den Hauptteil der Wandelemente (26) im Abstand zu der radial äußeren Wand (24) zu halten, und wobei die radial äußere Wand (24) gelocht ist, damit ein Kühlmittel in die Räume einströmen kann, die zwischen der radial äußeren Wand (24) und den Wandelementen (26) gebildet sind, und wobei jedes der Wandelemente (26) gelocht ist, damit das Kühlmittel aus den Räumen durch diese Löcher abströmen kann, und wobei Mittel (27) vorgesehen sind, um den Umfang eines jeden Wandelementes (26) mit der radial äußeren Wand (24) zu verbinden,
    dadurch gekennzeichnet, daß die Verbindungsmittel (27) eine kontinuierlich um den Umfang eines jeden Wandelementes (26) umlaufende Wand definieren, die einstückig mit dem Umfang hergestellt ist, so daß eine gesonderte Kammer (28) zwischen jedem Wandelement (26) und der radial äußeren Wand (24) gebildet wird, durch die das Kühlmittel strömen kann.
  2. Brennkammer für ein Gasturbinentriebwerk nach Anspruch 1,
    dadurch gekennzeichnet, daß die Löcher (30) in der radial äußeren Wand (24) so angeordnet sind, daß das Kühlmittel derart auf die Wandelemente (26) gerichtet wird, daß eine Aufprallkühlung erfolgt.
  3. Brennkammer für ein Gasturbinentriebwerk nach Anspruch 1 oder 2,
    dadurch gekennzeichnet, daß die Löcher (32) in den Wandelementen (26) so angeordnet sind, daß das Kühlmittel aus den gesonderten Kammern (28) derart ausströmt, daß eine Filmkühlung der Wandelemente (26) bewirkt wird.
  4. Brennkammer für ein Gasturbinentriebwerk nach Anspruch 3,
    dadurch gekennzeichnet, daß die Löcher (32) in den Wandelementen (26) in Richtung der Strömung durch die Brennkammer geneigt sind, um diese Filmkühlung der Wandelemente (26) zu gewährleisten.
  5. Brennkammer für ein Gasturbinentriebwerk nach Anspruch 4,
    dadurch gekennzeichnet, daß die Löcher (32) in den Wandelementen (26) einen rennstreckenförmigen Querschnitt besitzen.
  6. Brennkammer für ein Gasturbinentriebwerk nach einem der vorhergehenden Ansprüche,
    dadurch gekennzeichnet, daß die Wandelemente (26) derart an der Außenwand (24) angeordnet sind, daß sie allgemein benachbart zueinander liegen.
  7. Brennkammer für ein Gasturbinentriebwerk nach Anspruch 1,
    dadurch gekennzeichnet, daß der Umfangsflansch (27) an jedem Wandelement (26) außerdem die Mittel bildet, um das zugeordnete Wandelement (26) im Abstand zu der Außenwand (24) zu halten.
  8. Brennkammer für ein Gasturbinentriebwerk nach einem der vorhergehenden Ansprüche,
    dadurch gekennzeichnet, daß jedes der Wandelemente (26) mit integralen Bolzen (29) versehen ist, um ihre Befestigung an der Außenwand (24) zu ermöglichen.
  9. Brennkammer für ein Gasturbinentriebwerk nach einem der vorhergehenden Ansprüche,
    dadurch gekennzeichnet, daß jedes der Wandelemente (26) mit mehreren Ständern (33) versehen ist, um die Wärmeaustauschbeziehung zwischen den Wandelementen (26) und der Kühlmittelströmung durch die Räume (28) zwischen den Wandelementen (26) und der Außenwand (24) zu verbessern.
  10. Brennkammer für ein Gasturbinentriebwerk nach Anspruch 9,
    dadurch gekennzeichnet, daß jeder Ständer (33) an der Außenwand (24) angreift.
EP92904247A 1991-03-22 1992-02-03 Gasturbinenbrennkammer Expired - Lifetime EP0576435B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB919106085A GB9106085D0 (en) 1991-03-22 1991-03-22 Gas turbine engine combustor
GB91060855 1991-03-22
PCT/GB1992/000201 WO1992016798A1 (en) 1991-03-22 1992-02-03 Gas turbine engine combustor

Publications (2)

Publication Number Publication Date
EP0576435A1 EP0576435A1 (de) 1994-01-05
EP0576435B1 true EP0576435B1 (de) 1995-08-23

Family

ID=10692006

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92904247A Expired - Lifetime EP0576435B1 (de) 1991-03-22 1992-02-03 Gasturbinenbrennkammer

Country Status (5)

Country Link
EP (1) EP0576435B1 (de)
JP (1) JPH06507468A (de)
DE (1) DE69204280T2 (de)
GB (1) GB9106085D0 (de)
WO (1) WO1992016798A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2508803A2 (de) 2011-04-06 2012-10-10 Rolls-Royce plc Gekühlter doppelwandiger Artikel
DE102013226488A1 (de) 2013-12-18 2015-06-18 Rolls-Royce Deutschland Ltd & Co Kg Unterlegscheibe einer Brennkammerschindel einer Gasturbine
DE102016222099A1 (de) 2016-11-10 2018-05-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2723177B1 (fr) * 1994-07-27 1996-09-06 Snecma Chambre de combustion comportant une double paroi
GB2298266A (en) * 1995-02-23 1996-08-28 Rolls Royce Plc A cooling arrangement for heat resistant tiles in a gas turbine engine combustor
US5758503A (en) * 1995-05-03 1998-06-02 United Technologies Corporation Gas turbine combustor
DE19516798A1 (de) * 1995-05-08 1996-11-14 Abb Management Ag Vormischbrenner mit axialer oder radialer Luftzuströmung
FR2752916B1 (fr) * 1996-09-05 1998-10-02 Snecma Chemise de protection thermique pour chambre de combustion de turboreacteur
US6079199A (en) * 1998-06-03 2000-06-27 Pratt & Whitney Canada Inc. Double pass air impingement and air film cooling for gas turbine combustor walls
DE102007018061A1 (de) 2007-04-17 2008-10-23 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand
US20100263386A1 (en) * 2009-04-16 2010-10-21 General Electric Company Turbine engine having a liner
DE102009032277A1 (de) 2009-07-08 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerkopf einer Gasturbine
CH703657A1 (de) * 2010-08-27 2012-02-29 Alstom Technology Ltd Verfahren zum betrieb einer brenneranordnung sowie brenneranordnung zur durchführung des verfahrens.
JP2012145098A (ja) * 2010-12-21 2012-08-02 Toshiba Corp トランジションピースおよびガスタービン
US20120180492A1 (en) * 2011-01-14 2012-07-19 General Electric Company Apparatus for vibration support in combustors and method for forming apparatus
EP2559942A1 (de) 2011-08-19 2013-02-20 Rolls-Royce Deutschland Ltd & Co KG Brennkammerkopf einer Gasturbine mit Kühlung und Dämpfung
JP5821550B2 (ja) * 2011-11-10 2015-11-24 株式会社Ihi 燃焼器ライナ
DE102012016493A1 (de) 2012-08-21 2014-02-27 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit prallgekühlten Bolzen der Brennkammerschindeln
DE102012025375A1 (de) 2012-12-27 2014-07-17 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Anordnung von Prallkühllöchern und Effusionslöchern in einer Brennkammerwand einer Gasturbine
DE102013003444A1 (de) 2013-02-26 2014-09-11 Rolls-Royce Deutschland Ltd & Co Kg Prall-effusionsgekühlte Schindel einer Gasturbinenbrennkammer mit verlängerten Effusionsbohrungen
DE102013222932A1 (de) 2013-11-11 2015-05-28 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit Schindel zur Durchführung einer Zündkerze
JP2024091028A (ja) * 2022-12-23 2024-07-04 川崎重工業株式会社 ガスタービンの燃焼器

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1093515A (en) * 1966-04-06 1967-12-06 Rolls Royce Method of producing combustion chambers and similar components for gas turbine engines
US3422620A (en) * 1967-05-04 1969-01-21 Westinghouse Electric Corp Combustion apparatus
GB1552132A (en) * 1975-11-29 1979-09-12 Rolls Royce Combustion chambers for gas turbine engines
GB2087065B (en) * 1980-11-08 1984-11-07 Rolls Royce Wall structure for a combustion chamber
US4422300A (en) * 1981-12-14 1983-12-27 United Technologies Corporation Prestressed combustor liner for gas turbine engine
GB2204672B (en) * 1987-05-06 1991-03-06 Rolls Royce Plc Combustor
GB2221979B (en) * 1988-08-17 1992-03-25 Rolls Royce Plc A combustion chamber for a gas turbine engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2508803A2 (de) 2011-04-06 2012-10-10 Rolls-Royce plc Gekühlter doppelwandiger Artikel
US9010124B2 (en) 2011-04-06 2015-04-21 Rolls-Royce Plc Cooled double walled article
DE102013226488A1 (de) 2013-12-18 2015-06-18 Rolls-Royce Deutschland Ltd & Co Kg Unterlegscheibe einer Brennkammerschindel einer Gasturbine
EP2886961A1 (de) 2013-12-18 2015-06-24 Rolls-Royce Deutschland Ltd & Co KG Unterlegscheibe einer Brennkammerschindel einer Gasturbine
DE102016222099A1 (de) 2016-11-10 2018-05-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine

Also Published As

Publication number Publication date
EP0576435A1 (de) 1994-01-05
GB9106085D0 (en) 1991-05-08
DE69204280D1 (de) 1995-09-28
WO1992016798A1 (en) 1992-10-01
JPH06507468A (ja) 1994-08-25
DE69204280T2 (de) 1996-01-25

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