EP0813669A1 - Agencement d'ecran thermique pour chambres de combustion de turbines a gaz - Google Patents

Agencement d'ecran thermique pour chambres de combustion de turbines a gaz

Info

Publication number
EP0813669A1
EP0813669A1 EP96906722A EP96906722A EP0813669A1 EP 0813669 A1 EP0813669 A1 EP 0813669A1 EP 96906722 A EP96906722 A EP 96906722A EP 96906722 A EP96906722 A EP 96906722A EP 0813669 A1 EP0813669 A1 EP 0813669A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
web
guide rib
combustion chamber
air
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
EP96906722A
Other languages
German (de)
English (en)
Other versions
EP0813669B1 (fr
Inventor
William Kwan
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
BMW Rolls Royce GmbH
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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Publication of EP0813669A1 publication Critical patent/EP0813669A1/fr
Application granted granted Critical
Publication of EP0813669B1 publication Critical patent/EP0813669B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/28—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
    • 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

Definitions

  • the invention relates to a heat shield arrangement for a gas turbine combustion chamber with a heat shield with a central passage opening for a burner and with a web running around the edge of the passage opening and having a plurality of air passage openings for the cold rear side of the heat shield facing away from the combustion chamber has introduced cooling air.
  • a heat shield arrangement for a gas turbine combustion chamber with a heat shield with a central passage opening for a burner and with a web running around the edge of the passage opening and having a plurality of air passage openings for the cold rear side of the heat shield facing away from the combustion chamber has introduced cooling air.
  • the present heat shield is preferably provided for an annular combustion chamber.
  • the hot surface must be cooled intensively, for which purpose the usual heat shields have a multiplicity of cooling air passage openings, via which the cooling air flow brought up to the cold rear side of the heat shield can pass through the heat shield and then place a cooling air film on the hot surface of the heat shield.
  • the cooling air flow portion exiting in the area of the passage opening via the gap between a sealing part receiving the burner and the heat shield is also not sufficient for this.
  • the object of the invention is therefore to identify measures by means of which the cooling of the heat shield, in particular in the area of the burner passage opening, can be further improved.
  • the solution to this problem is characterized by a guide rib provided inside the passage opening and oriented essentially parallel to the web, the combustion chamber end of which is angled around the cooling air flow flowing into the gap between the web and guide rib via the air transfer openings in the direction of the hot surface of the heat shield redirect.
  • FIG. 5a shows a further variant
  • FIG. 5b shows the partial section A from FIG. 5a.
  • the cold rear of the heat shield 1 is provided with the reference number 2a, while the hot surface of the heat shield facing the combustion chamber bears the reference number 2b.
  • this heat shield surrounds a burner, not shown, via which a fuel-air stream is introduced into the combustion chamber of the gas turbine.
  • the heat shield has a passage opening 3 for the burner.
  • the burner is surrounded by a sealing part 4.
  • a bolt 5 which protrudes from the heat shield 1 behind the passage opening 3 and serves to fasten the heat shield 1 to the combustion chamber head of the gas turbine.
  • the hot surface 2b of the heat shield must be cooled intensively.
  • a cooling air flow is brought to the cold rear side 2a of the heat shield 1, which (as FIG. 1 shows) can at least partially penetrate through a plurality of bores 6 in the heat shield 1 and - since these bores 6 are inclined with respect to the surface 2b - Lies as a cooling air film on the hot surface 2b of the heat shield 1.
  • a plurality of air transfer openings 7 are likewise provided in a web 8, which is provided at the edge of the passage opening 3, in particular in the area of the rear side 2a. Cooling air can thus get from the rear side 2a into the area of the passage opening 3 via these air transfer openings 7.
  • the web 8 is part of the heat shield 1, and in the other exemplary embodiments the web 8 is part of a separate ring element 11.
  • a guide rib 9 is provided which is oriented essentially parallel to the web 8 and whose end 9a on the combustion side is such it is angled that the cooling air flow is deflected in the direction of the hot surface 2b of the heat shield 1 as shown by the arrow 10.
  • the free end 9a of the guide rib 9 is substantially parallel to the chamfered edge la of the heat shield 1 in the corner region of through opening 3 and hot surface 2b aligned (see. Fig. 1).
  • the guide rib 9 is molded onto a so-called ring element 11, which is arranged between a collar 4 'of the sealing part 4 and the web 8 molded onto the heat shield 1.
  • This ring element 11 can thus be manufactured simply on the one hand and on the other hand simply plugged onto the heat shield 1, which is also easy to manufacture.
  • a ring element 11 is also provided between the collar 4 and the heat shield 1, which in this case forms the web 8 and has the air transfer openings 7.
  • the guide rib 9, which also represents a separate annular component, is also supported on this ring element 11.
  • the air transfer openings 7 in the ring element 11 are provided with swirling devices so that a desired vortex can be impressed on the cooling air flow passing through the air transfer openings 7.
  • 3 shows a similar embodiment with air transfer openings 7 without swirling measures.
  • the guide rib 9 is thus molded onto the heat shield 1.
  • the heat shield 1 with the integrally formed guide rib 9 constitutes a cast part for this purpose.
  • the free end 9a of the guide rib 9 is so far into the Combustion chamber of the gas turbine pulled in that this free end 9a itself is aligned parallel to the hot surface 2b of the heat shield 1. In this way, the one in the annular gap 12 is urgent flow of cooling air is guided particularly safely and reliably onto the heat shield surface 2b.
  • the air transfer bores 7 are again provided with swirling devices, which is represented by the cross grating.
  • FIG. 5a, 5b show a further exemplary embodiment in which the guide rib 9 is molded onto the ring element 11 in a manner similar to the exemplary embodiment according to FIG. 1.
  • the air transfer openings 7 are located in the ring element 11, so that further measures are necessary in order to allow air access to these air transfer openings 7. Therefore, between the ring element 11 and the collar 4 'of the sealing part 4, there is a ring 13 slotted like a gear wheel, the tooth slots 13' of which allow this air access to the air transfer openings 7.
  • a spacer 14 provided with air passage openings 14 ' is shown, by means of which the sealing part 4 with its collar' is supported on the top wall 15 of the combustion chamber.
  • the cooling air flow brought to the side of the web 8 facing away from the combustion chamber ie. H. the cooling air flow must first penetrate the air passage openings 14 'in order to then be able to flow through the air passage openings 7 into the annular gap 12 between the web 8 and the guide rib 9, in order ultimately to lead from this guide rib 9 in the direction of the hot surface 2b of the heat shield 1 to be redirected.

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)
  • Spray-Type Burners (AREA)
  • Supercharger (AREA)

Abstract

Afin de refroidir aussi efficacement que possible la surface chaude de l'écran thermique (1) qui entoure le brûleur de la chambre de combustion annulaire d'une turbine à gaz, notamment dans la zone de l'orifice (3) du brûleur, un courant d'air de refroidissement (10), évacué en direction de l'orifice de passage par-dessus un élément jointif continu (8) situé au bord de l'orifice de passage, est guidé par une nervure de guidage (9) sensiblement parallèle à l'élément jointif (8). La nervure de guidage (9) comprend du côté de la chambre de combustion une extrémité coudée de sorte que le courant d'air de refroidissement qui pénètre entre l'élément jointif et la nervure de guidage soit dévié à cet endroit en direction de la surface chaude (2b) de l'écran thermique (1).
EP96906722A 1995-03-08 1996-03-01 Agencement d'ecran thermique pour chambres de combustion de turbines a gaz Expired - Lifetime EP0813669B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19508111A DE19508111A1 (de) 1995-03-08 1995-03-08 Hitzeschild-Anordnung für eine Gasturbinen-Brennkammer
DE19508111 1995-03-08
PCT/EP1996/000860 WO1996027765A1 (fr) 1995-03-08 1996-03-01 Agencement d'ecran thermique pour chambres de combustion de turbines a gaz

Publications (2)

Publication Number Publication Date
EP0813669A1 true EP0813669A1 (fr) 1997-12-29
EP0813669B1 EP0813669B1 (fr) 1999-09-22

Family

ID=7755962

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96906722A Expired - Lifetime EP0813669B1 (fr) 1995-03-08 1996-03-01 Agencement d'ecran thermique pour chambres de combustion de turbines a gaz

Country Status (5)

Country Link
US (1) US5894732A (fr)
EP (1) EP0813669B1 (fr)
CA (1) CA2214691A1 (fr)
DE (2) DE19508111A1 (fr)
WO (1) WO1996027765A1 (fr)

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EP1767855A1 (fr) * 2005-09-27 2007-03-28 Siemens Aktiengesellschaft Chambre de combustion et turbine à gaz
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US20100089020A1 (en) * 2008-10-14 2010-04-15 General Electric Company Metering of diluent flow in combustor
US9121609B2 (en) * 2008-10-14 2015-09-01 General Electric Company Method and apparatus for introducing diluent flow into a combustor
US20100089022A1 (en) * 2008-10-14 2010-04-15 General Electric Company Method and apparatus of fuel nozzle diluent introduction
US8567199B2 (en) * 2008-10-14 2013-10-29 General Electric Company Method and apparatus of introducing diluent flow into a combustor
US8448416B2 (en) * 2009-03-30 2013-05-28 General Electric Company Combustor liner
US8695322B2 (en) * 2009-03-30 2014-04-15 General Electric Company Thermally decoupled can-annular transition piece
US8863527B2 (en) * 2009-04-30 2014-10-21 Rolls-Royce Corporation Combustor liner
JP4838888B2 (ja) * 2009-05-27 2011-12-14 川崎重工業株式会社 ガスタービン燃焼器
DE102009033592A1 (de) 2009-07-17 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit Starterfilm zur Kühlung der Brennkammerwand
EP2530383B1 (fr) * 2010-01-28 2019-09-18 Kawasaki Jukogyo Kabushiki Kaisha Chambre de combustion de turbine à gaz
GB201107090D0 (en) * 2011-04-28 2011-06-08 Rolls Royce Plc A head part of an annular combustion chamber
GB201107095D0 (en) 2011-04-28 2011-06-08 Rolls Royce Plc A head part of an annular combustion chamber
JP5924618B2 (ja) * 2012-06-07 2016-05-25 川崎重工業株式会社 燃料噴射装置
WO2014163669A1 (fr) 2013-03-13 2014-10-09 Rolls-Royce Corporation Ensemble chambre de combustion pour turbine à gaz
DE102013007443A1 (de) * 2013-04-30 2014-10-30 Rolls-Royce Deutschland Ltd & Co Kg Brennerdichtung für Gasturbinen-Brennkammerkopf und Hitzeschild
FR3019216B1 (fr) * 2014-03-31 2018-08-10 Safran Aircraft Engines Deflecteur de fond de chambre de combustion d'une turbomachine comportant des rainures sur le pourtour d'une ouverture centrale
US20160116169A1 (en) * 2014-09-29 2016-04-28 United Technologies Corporation Mixer retention
FR3026827B1 (fr) * 2014-10-01 2019-06-07 Safran Aircraft Engines Chambre de combustion de turbomachine
US9933161B1 (en) * 2015-02-12 2018-04-03 Pratt & Whitney Canada Corp. Combustor dome heat shield
US9746184B2 (en) * 2015-04-13 2017-08-29 Pratt & Whitney Canada Corp. Combustor dome heat shield
US10267521B2 (en) 2015-04-13 2019-04-23 Pratt & Whitney Canada Corp. Combustor heat shield
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
GB201701380D0 (en) 2016-12-20 2017-03-15 Rolls Royce Plc A combustion chamber and a combustion chamber fuel injector seal
GB201715366D0 (en) 2017-09-22 2017-11-08 Rolls Royce Plc A combustion chamber
US10330204B2 (en) 2017-11-10 2019-06-25 Rolls-Royce Deutschland Ltd & Co Kg Burner seal of a gas turbine and method for manufacturing the same
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Also Published As

Publication number Publication date
EP0813669B1 (fr) 1999-09-22
US5894732A (en) 1999-04-20
WO1996027765A1 (fr) 1996-09-12
CA2214691A1 (fr) 1996-09-12
DE59603160D1 (de) 1999-10-28
DE19508111A1 (de) 1996-09-12

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