EP0813669A1 - Hitzeschild-anordnung für eine gasturbinen-brennkammer - Google Patents
Hitzeschild-anordnung für eine gasturbinen-brennkammerInfo
- 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
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
Description
Claims
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 (de) | 1995-03-08 | 1996-03-01 | Hitzeschild-anordnung für eine gasturbinen-brennkammer |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0813669A1 true EP0813669A1 (de) | 1997-12-29 |
EP0813669B1 EP0813669B1 (de) | 1999-09-22 |
Family
ID=7755962
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP96906722A Expired - Lifetime EP0813669B1 (de) | 1995-03-08 | 1996-03-01 | Hitzeschild-anordnung für eine gasturbinen-brennkammer |
Country Status (5)
Country | Link |
---|---|
US (1) | US5894732A (de) |
EP (1) | EP0813669B1 (de) |
CA (1) | CA2214691A1 (de) |
DE (2) | DE19508111A1 (de) |
WO (1) | WO1996027765A1 (de) |
Families Citing this family (61)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19643028A1 (de) * | 1996-10-18 | 1998-04-23 | Bmw Rolls Royce Gmbh | Brennkammer einer Gasturbine mit einem ringförmigen Kopfabschnitt |
GB9623195D0 (en) * | 1996-11-07 | 1997-01-08 | Rolls Royce Plc | Gas turbine engine combustor |
US6546732B1 (en) * | 2001-04-27 | 2003-04-15 | General Electric Company | Methods and apparatus for cooling gas turbine engine combustors |
US6530227B1 (en) * | 2001-04-27 | 2003-03-11 | General Electric Co. | Methods and apparatus for cooling gas turbine engine combustors |
US6497105B1 (en) | 2001-06-04 | 2002-12-24 | Pratt & Whitney Canada Corp. | Low cost combustor burner collar |
US6546733B2 (en) * | 2001-06-28 | 2003-04-15 | General Electric Company | Methods and systems for cooling gas turbine engine combustors |
DE10214573A1 (de) * | 2002-04-02 | 2003-10-16 | Rolls Royce Deutschland | Brennkammer einer Gasturbine mit Starterfilmkühlung |
US6751961B2 (en) * | 2002-05-14 | 2004-06-22 | United Technologies Corporation | Bulkhead panel for use in a combustion chamber of a gas turbine engine |
US6792757B2 (en) | 2002-11-05 | 2004-09-21 | Honeywell International Inc. | Gas turbine combustor heat shield impingement cooling baffle |
US6871501B2 (en) * | 2002-12-03 | 2005-03-29 | General Electric Company | Method and apparatus to decrease gas turbine engine combustor emissions |
US6904676B2 (en) | 2002-12-04 | 2005-06-14 | General Electric Company | Methods for replacing a portion of a combustor liner |
US8021784B2 (en) * | 2004-03-23 | 2011-09-20 | Hammond Group, Inc. | Cureless battery paste and method for producing battery plates |
US7140185B2 (en) * | 2004-07-12 | 2006-11-28 | United Technologies Corporation | Heatshielded article |
US7140189B2 (en) * | 2004-08-24 | 2006-11-28 | Pratt & Whitney Canada Corp. | Gas turbine floating collar |
US7134286B2 (en) * | 2004-08-24 | 2006-11-14 | Pratt & Whitney Canada Corp. | Gas turbine floating collar arrangement |
EP1767855A1 (de) * | 2005-09-27 | 2007-03-28 | Siemens Aktiengesellschaft | Brennkammer und Gasturbinenanlage |
FR2893390B1 (fr) * | 2005-11-15 | 2011-04-01 | Snecma | Fond de chambre de combustion avec ventilation |
FR2894327B1 (fr) * | 2005-12-05 | 2008-05-16 | Snecma Sa | Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif |
GB2434199B (en) * | 2006-01-14 | 2011-01-05 | Alstom Technology Ltd | Combustor liner with heat shield |
US7596949B2 (en) * | 2006-02-23 | 2009-10-06 | General Electric Company | Method and apparatus for heat shielding gas turbine engines |
FR2903172B1 (fr) * | 2006-06-29 | 2008-10-17 | Snecma Sa | Agencement pour chambre de combustion de turbomachine ayant un defecteur a collerette |
FR2903171B1 (fr) * | 2006-06-29 | 2008-10-17 | Snecma Sa | Agencement a liaison par crabot pour chambre de combustion de turbomachine |
US7827800B2 (en) * | 2006-10-19 | 2010-11-09 | Pratt & Whitney Canada Corp. | Combustor heat shield |
US7721548B2 (en) * | 2006-11-17 | 2010-05-25 | Pratt & Whitney Canada Corp. | Combustor liner and heat shield assembly |
US7681398B2 (en) * | 2006-11-17 | 2010-03-23 | Pratt & Whitney Canada Corp. | Combustor liner and heat shield assembly |
US7748221B2 (en) * | 2006-11-17 | 2010-07-06 | Pratt & Whitney Canada Corp. | Combustor heat shield with variable cooling |
US7861530B2 (en) * | 2007-03-30 | 2011-01-04 | Pratt & Whitney Canada Corp. | Combustor floating collar with louver |
US7926280B2 (en) * | 2007-05-16 | 2011-04-19 | Pratt & Whitney Canada Corp. | Interface between a combustor and fuel nozzle |
FR2918443B1 (fr) * | 2007-07-04 | 2009-10-30 | Snecma Sa | Chambre de combustion comportant des deflecteurs de protection thermique de fond de chambre et moteur a turbine a gaz en etant equipe |
GB2460403B (en) * | 2008-05-28 | 2010-11-17 | Rolls Royce Plc | Combustor Wall with Improved Cooling |
US20100089020A1 (en) * | 2008-10-14 | 2010-04-15 | General Electric Company | Metering of diluent flow in combustor |
US8567199B2 (en) * | 2008-10-14 | 2013-10-29 | General Electric Company | Method and apparatus of introducing diluent flow into a 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 |
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 (de) * | 2010-01-28 | 2019-09-18 | Kawasaki Jukogyo Kabushiki Kaisha | Gasturbinenbrennkammer |
GB201107095D0 (en) | 2011-04-28 | 2011-06-08 | Rolls Royce Plc | A head part of an annular combustion chamber |
GB201107090D0 (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 (en) | 2013-03-13 | 2014-10-09 | Rolls-Royce Corporation | Combustor assembly for a gas turbine engine |
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 |
EP3483503B1 (de) * | 2017-11-10 | 2021-01-06 | Rolls-Royce Deutschland Ltd & Co KG | Brennerdichtung einer gasturbine und verfahren zu deren herstellung |
DE102018106051A1 (de) | 2018-03-15 | 2019-09-19 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammerbaugruppe mit Brennerdichtung und Düse sowie einer Leitströmungserzeugungseinrichtung |
FR3081974B1 (fr) * | 2018-06-04 | 2020-06-19 | Safran Aircraft Engines | Chambre de combustion d'une turbomachine |
FR3082284B1 (fr) * | 2018-06-07 | 2020-12-11 | Safran Aircraft Engines | Chambre de combustion pour une turbomachine |
DE102018125698A1 (de) | 2018-10-17 | 2020-04-23 | Man Energy Solutions Se | Gasturbinenbrennkammer |
US11892165B2 (en) | 2021-05-19 | 2024-02-06 | General Electric Company | Heat shield for fuel nozzle |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
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US4180974A (en) * | 1977-10-31 | 1980-01-01 | General Electric Company | Combustor dome sleeve |
GB1594463A (en) * | 1978-02-07 | 1981-07-30 | Rolls Royce | Combustion equipment |
DE2949726A1 (de) * | 1979-12-11 | 1981-06-19 | Hochtemperatur-Reaktorbau GmbH, 5000 Köln | Von einem gas hohen druckes und hoher temperatur durchstroemter gaskanal grosser abmessungen |
US4322945A (en) * | 1980-04-02 | 1982-04-06 | United Technologies Corporation | Fuel nozzle guide heat shield for a gas turbine engine |
DE3131310A1 (de) * | 1981-08-07 | 1983-02-24 | Deutsche Babcock Bau GmbH, 4200 Oberhausen | Feuerungsraum fuer eine verbrennungsanlage |
EP0153842B1 (de) * | 1984-02-29 | 1988-07-27 | LUCAS INDUSTRIES public limited company | Brennkammer für Gasturbinen |
US4934145A (en) * | 1988-10-12 | 1990-06-19 | United Technologies Corporation | Combustor bulkhead heat shield assembly |
DE9000548U1 (de) * | 1990-01-19 | 1990-03-01 | Klöckner-Humboldt-Deutz AG, 5000 Köln | Wärmeschutz-Vorrichtung |
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 |
GB9112324D0 (en) * | 1991-06-07 | 1991-07-24 | Rolls Royce Plc | Gas turbine engine combustor |
CA2070518C (en) * | 1991-07-01 | 2001-10-02 | Adrian Mark Ablett | Combustor dome assembly |
GB2287310B (en) * | 1994-03-01 | 1997-12-03 | Rolls Royce Plc | Gas turbine engine combustor heatshield |
US5623827A (en) * | 1995-01-26 | 1997-04-29 | General Electric Company | Regenerative cooled dome assembly for a gas turbine engine combustor |
-
1995
- 1995-03-08 DE DE19508111A patent/DE19508111A1/de not_active Withdrawn
-
1996
- 1996-03-01 CA CA002214691A patent/CA2214691A1/en not_active Abandoned
- 1996-03-01 US US08/913,122 patent/US5894732A/en not_active Expired - Fee Related
- 1996-03-01 EP EP96906722A patent/EP0813669B1/de not_active Expired - Lifetime
- 1996-03-01 DE DE59603160T patent/DE59603160D1/de not_active Expired - Fee Related
- 1996-03-01 WO PCT/EP1996/000860 patent/WO1996027765A1/de active IP Right Grant
Non-Patent Citations (1)
Title |
---|
See references of WO9627765A1 * |
Also Published As
Publication number | Publication date |
---|---|
DE59603160D1 (de) | 1999-10-28 |
WO1996027765A1 (de) | 1996-09-12 |
US5894732A (en) | 1999-04-20 |
CA2214691A1 (en) | 1996-09-12 |
EP0813669B1 (de) | 1999-09-22 |
DE19508111A1 (de) | 1996-09-12 |
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