[go: up one dir, main page]

EP1651841B1 - Composant ouvert refroidi destine a une turbine a gaz, chambre de combustion et turbine a gaz - Google Patents

Composant ouvert refroidi destine a une turbine a gaz, chambre de combustion et turbine a gaz Download PDF

Info

Publication number
EP1651841B1
EP1651841B1 EP04739955A EP04739955A EP1651841B1 EP 1651841 B1 EP1651841 B1 EP 1651841B1 EP 04739955 A EP04739955 A EP 04739955A EP 04739955 A EP04739955 A EP 04739955A EP 1651841 B1 EP1651841 B1 EP 1651841B1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
cavity
component
wall
combustion chamber
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
EP04739955A
Other languages
German (de)
English (en)
Other versions
EP1651841A1 (fr
Inventor
Stefan Hoffmann
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to PL04739955T priority Critical patent/PL1651841T3/pl
Priority to EP04739955A priority patent/EP1651841B1/fr
Publication of EP1651841A1 publication Critical patent/EP1651841A1/fr
Application granted granted Critical
Publication of EP1651841B1 publication Critical patent/EP1651841B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • 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
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer

Definitions

  • the present invention relates to an open-cooled component for a gas turbine having a H adoptedgasbeetzmannten outer wall which at least partially defines a first cavity for a first means and are arranged in the through holes, which open through openings in the cavity and on the other hand in the hot gas space and at least one second cavity for admixing a second means in fluid communication with the passage openings.
  • the invention further relates to a combustion chamber and a gas turbine.
  • Combustor walls as well as gas turbine blades are subject to high physical stress during normal operation of the gas turbine.
  • these components are provided with a cooling. If air is used as a coolant, it is taken from a combustion chamber upstream compressor with diffuser and is lost to the combustion process. As a result, flame temperatures and NO x emissions increase.
  • the wall of a combustion chamber is cooled either open or closed.
  • the open cooling is designed as convective cooling, film cooling or as impingement cooling with a cooling air outlet in the combustion chamber.
  • the closed cooling requires a higher design effort and leads to an increased pressure loss due to the cooling air flow and the cooling itself.
  • cooling air extraction In order to reduce the negative effect caused by the cooling air extraction, it is known to add fuel. In the prior art, this is as cooling air reheating or further Meaning also known as stepped combustion.
  • a combustion chamber of a gas turbine with a plurality of hollow freestanding spokes known in the cavity of a fuel is performed.
  • the cavity is connected through openings with the combustion chamber.
  • air is supplied to the ports in a supply passage disposed in the outer wall of the spokes to receive, in conjunction with the fuel, a combustible mixture which is fed into the combustion chamber for NO x reduction during operation of the gas turbine.
  • a disadvantage of the known concepts is that for the mixing of cooling air and fuel, a volume is to be provided by the reactants by self-ignition or ignite flashback in the components. As a result, under certain circumstances, stable combustion processes develop, so that the cooling effect of the fuel-air mixture is lost or the component can be damaged by the internal combustion occurring.
  • the second cavity is formed by supply channels provided in the outer wall, which are connected via transverse channels with the through holes formed as a through-hole, so that the two means are miscible only within the through holes.
  • the invention further proposes a combustion chamber for a gas turbine with a wall element, which has a corresponding arrangement.
  • the invention turns away.
  • This allows the previously formed between the double wall second cavity be embedded as a supply channel in the outer wall, which is connected via separate transverse channels with the through holes.
  • a possibility is thus created for the first time to substantially completely avoid a mixing volume in the component, as a result of which flashback and auto-ignition in the component can be largely avoided.
  • a flame temperature increase can be reduced with open cooling, since the cooling air can now be enriched with fuel without the disadvantages described above.
  • the present invention therefore allows the cooling air flow to be increased without adversely affecting combustion.
  • the passage opening can be provided, for example, for the cooling air to flow into the combustion chamber of the combustion chamber.
  • fuel Via the supply channel provided in the outer wall of the component, fuel can be supplied which mixes with the cooling air as it flows into the passage opening and thus forms a combustible mixture.
  • a flashback is avoided insofar as there is no ignitable mixture in one of the supply channels or in the cavities before the mouth of the transverse channel in the passage opening.
  • the outer wall has a multiplicity of through-bores, a multiplicity of supply channels extending between the bores, and a multiplicity of further transverse channels crosslinking the supply channels with the through-bores. Due to the net-like structure of the channels and holes, a homogenization of the flowing mixture into the combustion chamber of fuel and cooling air can be achieved. About that In addition, it is possible to cool the component more uniformly, so that local overheating can be avoided.
  • the component has at least two interconnectable layers.
  • one layer may have the channel, while a second layer is formed on the combustion chamber side of a particularly resistant material.
  • a high load capacity of the component can be achieved.
  • the channel is introduced in at least one layer surface of one of the layers on the connection side.
  • the channel can be introduced in this way by milling or similar material-removing processes in the surface of a layer, wherein by assembling the adjacent layers closed channels are formed.
  • the channel can thereby be introduced into the component by means of known and also cost-effective methods.
  • the cavity with a first fluid source and the supply channel with a second fluid source is connectable.
  • Both fluids ie means, can be used to cool the blade so as to reduce the amount of air required for cooling. A larger amount of air is available to the combustion process, so that high flame temperatures and NO x emissions can be reduced.
  • the blade is basically the same principle as for the wall element of the combustion chamber at the bottom. Again, there is essentially no mixing volume, so that flashback and autoignition are largely avoided. The reliability of the gas turbine with respect to defective blades can be increased. As with the combustion chamber, the cooling air flow can be increased without negative effects on the combustion and the flame acoustics are detuned.
  • the invention also proposes that one of the two fluid sources is an oxidant source and the other fluid source is a fuel source.
  • an ignitable mixture is formed only in the region of the mouth of the passage opening in the flow channel of the gas turbine, when the mouth of the channels is arranged sufficiently close to the mouth of the passage opening in the flow channel.
  • the invention also proposes a gas turbine, wherein the gas turbine has a combustion chamber according to the invention.
  • the negative effects, as described above, can be largely reduced by supplying fuel, wherein the combustion chamber according to the invention enables safe operation with respect to auto-ignition and flashback. Furthermore, it is advantageous to influence the flame acoustics in order to reduce the stresses and wear caused by this.
  • the invention also proposes a gas turbine with a component designed as a blade.
  • the cooling effect for the blade of the turbine unit which can be designed as a fixed guide blade as well as a rotating blade can be improved by increasing the cooling air flow, the negative effects on the combustion can be largely avoided.
  • an influence on the detuning of the flame acoustics can be exerted. Wear and tear can be further reduced.
  • Fig. 1 shows a section through an inventive designed as a wall element 2 component with a plurality of through holes 3, can enter through the cooling air into the combustion chamber.
  • the wall element 2 also has transverse channels 4, which open at one end in each case into a passage opening 3. Via connecting channels 9, a fluid fuel can be supplied, which is guided via the transverse channels 4 to the through holes 3 and is introduced there into the flow of cooling air.
  • Fig. 2 illustrates this system of channels for the fuel supply.
  • the wall element 2 has two interconnectable layers 6, 7. In the connection-side layer surface of the layer 6, the channel system is introduced by milling. By the connection of the layers 6 and 7 closed channels 4 and 9 are formed.
  • Fig. 3 shows a plan view of the surface of the layer 6 of the wall element 2 in which the channels 4 and 9 are introduced.
  • the connecting channel 9 is formed integrally with the wall element.
  • FIG. 4 schematically shows a section of a flow channel of a gas turbine, in which a blade 10 is arranged.
  • hot gas space 21 open through holes 12, wherein in the mouth region junctions of transverse channels 13 are indicated schematically.
  • FIG. 5 A section through such a blade 10 is shown in FIG. 5.
  • a blade wall 14 encloses a cavity 15, wherein the blade wall 17 is provided with passage openings 12. Cooling air can be supplied via the cavity 15 and exits through the passage openings 12 into the flow channel 11.
  • the blade wall 14 is further provided with a system of supply channels 13, which are connected via transverse channels 4 each with the through holes 12.
  • the supply channels 13 are in fluid communication with a fluid fuel source.
  • the blade 14 is constructed in two layers, consisting of an outer layer 16 and a cavity 15 forming inner layer 17.
  • the inner layer 17 has on its side facing the layer 16 by milling introduced recesses, which the channel system with the supply channels 13 form.
  • air is conducted as cooling air for the blade 10 via through holes 12 as oxidizing agent into the flow channel 11.
  • the fluid fuel is introduced into the passage openings 12 of the blade wall 14, so that an ignitable mixture is formed.
  • the ignitable mixture is formed only in the region of the mouth of the passage openings 3, 12 in the combustion chamber or the flow channel 11 of the gas turbine. In this way, a flashback is prevented in the respective channel system with the damage caused thereby.
  • Targeted variation of the fuel supply can also influence the flame acoustics. This also has an advantageous effect on the wear and the reliability of the gas turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un composant ouvert refroidi destiné à une turbine à gaz, comportant une paroi extérieure (20) recevant un gaz chaud, délimitant au moins partiellement une première cavité (15) destinée à un premier fluide et comportant des ouvertures de passage (3, 12), lesdites ouvertures de passage (3, 12) aboutissant d'une part dans la cavité (15) et d'autre part dans la chambre à gaz chaud (21). Ledit composant comporte également une deuxième cavité destinée au mélange d'un deuxième fluide, se trouvant en communication fluidique avec les ouvertures de passage (3, 12). L'invention vise à mettre en oeuvre un composant destiné à une turbine à gaz, permettant de réduire le retour de flamme et l'auto-allumage lors de l'apport de combustible dans l'air de refroidissement. A cet effet, la deuxième cavité est formée par des canaux d'alimentation (9, 13) pratiqués dans la paroi extérieure (20), reliés aux ouvertures de passage (3, 12) conçues en tant qu'alésages traversants par l'intermédiaire de canaux transversaux, de telle manière que les deux fluides ne se mélangent qu'à l'intérieur des alésages traversants. L'invention concerne également une chambre de combustion destinée à une turbine à gaz et une turbine à gaz comportant un tel composant.

Claims (10)

  1. Elément constitutif refroidi en circuit ouvert d'une turbine à gaz,
    comprenant une paroi (20) extérieure qui est soumise à du gaz chaud, qui délimite au moins en partie une première cavité (15) pour un premier fluide et dans laquelle sont ménagées des ouvertures (3, 12) de passage, lesquelles ouvertures (3, 12) de passage débouchent, d'une part, dans la cavité (15) et, d'autre part dans l'espace (21) pour du gaz chaud, ainsi que
    comprenant au moins une deuxième cavité de mélange d'un deuxième fluide qui communique avec les ouvertures (3, 12) de passage,
    caractérisé
    en ce que la deuxième cavité est formée par des canaux (9, 13) d'alimentation qui sont prévus dans la paroi extérieure, qui communiquent par des canaux (4) transversaux avec les ouvertures (3, 12) de passage constituées sous la forme de trou de passage, de façon à ce que les deux fluides ne puissent se mélanger qu'à l'intérieur des trous de passage.
  2. Elément constitutif suivant la revendication 1,
    caractérisé
    en ce que la paroi (20) extérieure a une pluralité de trous de passage, une pluralité de canaux (9, 13) d'alimentation s'étendant entre les trous et une pluralité d'autres canaux (4) transversaux mettant les canaux (9, 13) d'alimentation en réseau avec les trous de passage.
  3. Elément constitutif suivant la revendication 1 ou 2,
    caractérisé
    en ce que la paroi (2) extérieure a au moins deux couches (6, 7, 16, 17) pouvant être reliées mutuellement.
  4. Elément constitutif suivant la revendication 1, 2 ou 3,
    caractérisé
    en ce que les canaux (4, 9, 13) sont insérés entre les deux couches (6, 7) dans au moins une surface (6) de couche.
  5. Elément constitutif suivant l'une des revendications 1 à 4,
    caractérisé
    en ce que la première cavité (15) peut communiquer avec une première source de fluide et les canaux (9, 13) d'alimentation avec une deuxième source de fluide.
  6. Elément constitutif suivant la revendication 5,
    caractérisé
    en ce que l'une des deux sources de fluide est une source d'agent d'oxydation et l'autre source de fluide une source de combustible.
  7. Elément constitutif suivant l'une des revendications 1 à 4,
    caractérisé
    en ce que l'élément constitutif est un élément (2) de paroi d'une chambre de combustion ou d'une aube (10) d'une turbine à gaz.
  8. Chambre de combustion d'une turbine à gaz ayant un élément constitutif constitué en élément (2) de paroi suivant l'une des revendications 1 à 7.
  9. Turbine à gaz ayant une chambre de combustion suivant la revendication 8.
  10. Turbine à gaz ayant un élément constitutif constitué en aube suivant l'une des revendications 1 à 7.
EP04739955A 2003-07-04 2004-06-16 Composant ouvert refroidi destine a une turbine a gaz, chambre de combustion et turbine a gaz Expired - Lifetime EP1651841B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PL04739955T PL1651841T3 (pl) 2003-07-04 2004-06-16 Chłodzony w systemie otwartym element dla turbiny gazowej, komora spalania i turbina gazowa
EP04739955A EP1651841B1 (fr) 2003-07-04 2004-06-16 Composant ouvert refroidi destine a une turbine a gaz, chambre de combustion et turbine a gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03015216 2003-07-04
PCT/EP2004/006491 WO2005003517A1 (fr) 2003-07-04 2004-06-16 Composant ouvert refroidi destine a une turbine a gaz, chambre de combustion et turbine a gaz
EP04739955A EP1651841B1 (fr) 2003-07-04 2004-06-16 Composant ouvert refroidi destine a une turbine a gaz, chambre de combustion et turbine a gaz

Publications (2)

Publication Number Publication Date
EP1651841A1 EP1651841A1 (fr) 2006-05-03
EP1651841B1 true EP1651841B1 (fr) 2007-08-22

Family

ID=33560756

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04739955A Expired - Lifetime EP1651841B1 (fr) 2003-07-04 2004-06-16 Composant ouvert refroidi destine a une turbine a gaz, chambre de combustion et turbine a gaz

Country Status (7)

Country Link
US (2) US7658076B2 (fr)
EP (1) EP1651841B1 (fr)
CN (1) CN100353032C (fr)
DE (1) DE502004004752D1 (fr)
ES (1) ES2288687T3 (fr)
PL (1) PL1651841T3 (fr)
WO (1) WO2005003517A1 (fr)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1847684A1 (fr) 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Aube de turbine
EP1847696A1 (fr) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Composant pour un système de post-combustion dans une turbine à gaz et turbine à gaz associée.
US20080134685A1 (en) * 2006-12-07 2008-06-12 Ronald Scott Bunker Gas turbine guide vanes with tandem airfoils and fuel injection and method of use
US8291705B2 (en) * 2008-08-13 2012-10-23 General Electric Company Ultra low injection angle fuel holes in a combustor fuel nozzle
US9068743B2 (en) * 2009-02-26 2015-06-30 8 Rivers Capital, LLC & Palmer Labs, LLC Apparatus for combusting a fuel at high pressure and high temperature, and associated system
KR101648054B1 (ko) * 2009-02-26 2016-08-12 팔머 랩스, 엘엘씨 고온 및 고압에서 연료를 연소하는 장치 및 방법, 이에 관련된 시스템 및 장비
US8986002B2 (en) 2009-02-26 2015-03-24 8 Rivers Capital, Llc Apparatus for combusting a fuel at high pressure and high temperature, and associated system
US8397516B2 (en) * 2009-10-01 2013-03-19 General Electric Company Apparatus and method for removing heat from a gas turbine
US8894363B2 (en) 2011-02-09 2014-11-25 Siemens Energy, Inc. Cooling module design and method for cooling components of a gas turbine system
US8959886B2 (en) * 2010-07-08 2015-02-24 Siemens Energy, Inc. Mesh cooled conduit for conveying combustion gases
US8640974B2 (en) 2010-10-25 2014-02-04 General Electric Company System and method for cooling a nozzle
US9249977B2 (en) * 2011-11-22 2016-02-02 Mitsubishi Hitachi Power Systems, Ltd. Combustor with acoustic liner
US9284231B2 (en) 2011-12-16 2016-03-15 General Electric Company Hydrocarbon film protected refractory carbide components and use
DE102012205055B4 (de) * 2012-03-29 2020-08-06 Detlef Haje Gasturbinenbauteil für Hochtemperaturanwendungen, sowie Verfahren zum Betreiben und Herstellen eines solchen Gasturbinenbauteils
US9174309B2 (en) 2012-07-24 2015-11-03 General Electric Company Turbine component and a process of fabricating a turbine component
US9709274B2 (en) 2013-03-15 2017-07-18 Rolls-Royce Plc Auxetic structure with stress-relief features
EP2846096A1 (fr) * 2013-09-09 2015-03-11 Siemens Aktiengesellschaft Chambre de combustion tubulaire dotée d'une zone d'extrémité et turbine à gaz
DE102015111843A1 (de) 2015-07-21 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Turbine mit gekühlten Turbinenleitschaufeln
US20170176012A1 (en) * 2015-12-22 2017-06-22 General Electric Company Fuel injectors and staged fuel injection systems in gas turbines
AU2018229961B2 (en) 2017-03-07 2023-11-02 8 Rivers Capital, Llc System and method for operation of a flexible fuel combustor for a gas turbine
KR102554955B1 (ko) 2017-03-07 2023-07-12 8 리버스 캐피탈, 엘엘씨 고체 연료들 및 그 파생물들의 연소를 위한 시스템 및 방법
AU2019308815B2 (en) 2018-07-23 2024-12-19 8 Rivers Capital, Llc System and method for power generation with flameless combustion
CN113202566B (zh) * 2021-04-19 2022-12-02 中国航发湖南动力机械研究所 涡轮导向叶片及燃气涡轮发动机

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2647368A (en) * 1949-05-09 1953-08-04 Hermann Oestrich Method and apparatus for internally cooling gas turbine blades with air, fuel, and water
US2981066A (en) * 1956-04-12 1961-04-25 Elmer G Johnson Turbo machine
US3037351A (en) * 1956-05-14 1962-06-05 Paul O Tobeler Combustion turbine
US4347037A (en) * 1979-02-05 1982-08-31 The Garrett Corporation Laminated airfoil and method for turbomachinery
GB2049152B (en) * 1979-05-01 1983-05-18 Rolls Royce Perforate laminated material
US4302940A (en) * 1979-06-13 1981-12-01 General Motors Corporation Patterned porous laminated material
US4928481A (en) * 1988-07-13 1990-05-29 Prutech Ii Staged low NOx premix gas turbine combustor
US5405242A (en) * 1990-07-09 1995-04-11 United Technologies Corporation Cooled vane
US5125793A (en) * 1991-07-08 1992-06-30 The United States Of America As Represented By The Secretary Of The Air Force Turbine blade cooling with endothermic fuel
US5486093A (en) * 1993-09-08 1996-01-23 United Technologies Corporation Leading edge cooling of turbine airfoils
GB2310896A (en) 1996-03-05 1997-09-10 Rolls Royce Plc Air cooled wall
US6047550A (en) * 1996-05-02 2000-04-11 General Electric Co. Premixing dry low NOx emissions combustor with lean direct injection of gas fuel
DE19737845C2 (de) * 1997-08-29 1999-12-02 Siemens Ag Verfahren zum Herstellen einer Gasturbinenschaufel, sowie nach dem Verfahren hergestellte Gasturbinenschaufel
US20030024234A1 (en) * 2001-08-02 2003-02-06 Siemens Westinghouse Power Corporation Secondary combustor for low NOx gas combustion turbine
US7217088B2 (en) * 2005-02-02 2007-05-15 Siemens Power Generation, Inc. Cooling fluid preheating system for an airfoil in a turbine engine

Also Published As

Publication number Publication date
US8347632B2 (en) 2013-01-08
CN100353032C (zh) 2007-12-05
PL1651841T3 (pl) 2008-01-31
EP1651841A1 (fr) 2006-05-03
US20100083665A1 (en) 2010-04-08
ES2288687T3 (es) 2008-01-16
DE502004004752D1 (de) 2007-10-04
WO2005003517A1 (fr) 2005-01-13
US20070101722A1 (en) 2007-05-10
US7658076B2 (en) 2010-02-09
CN1806094A (zh) 2006-07-19

Similar Documents

Publication Publication Date Title
EP1651841B1 (fr) Composant ouvert refroidi destine a une turbine a gaz, chambre de combustion et turbine a gaz
DE3884751T2 (de) Gasgekühlter Flammenhalter.
DE69312362T2 (de) Brennkammer mit Verdünnungsleitschaufeln
EP2010757B1 (fr) Aube de turbine
DE69602804T2 (de) Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind
DE2143012C3 (de) Brenneranordnung bei einer Gasturbinen-Brennkammer
EP2156095B1 (fr) Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
DE112013007579B4 (de) Flüssigbrennstoffpatrone für eine Brennstoffdüse und Brennstoffdüse
EP2307806B1 (fr) Agencement de brûleur pour combustibles liquides et procédé de fabrication d'un agencement de brûleur
EP2359065A2 (fr) Lance à combustible pour brûleur
EP1847696A1 (fr) Composant pour un système de post-combustion dans une turbine à gaz et turbine à gaz associée.
DE102014117621A1 (de) Brennstoffinjektor mit Vormisch-Pilotdüse
DE602005001742T2 (de) Aerodynamisches aufschäumendes Brennstoff/Luft Einspritzungssystem für eine Gasturbinenbrennkammer
CH702737A2 (de) Brennkammer mit zwei Brennräumen.
EP1245806B1 (fr) Aube de turbine refroidie
EP1319895A2 (fr) Brûleur à prémélange à combustion pauvre pour turbine à gaz et son procédé de fonctionnement
EP2014978A1 (fr) Utilisation de gaz inertes destinés à isoler l'oxydant du combustible
DE112019000871B4 (de) Brennkammer und damit ausgestattete gasturbine
DE2730791A1 (de) Brennkammer fuer gasturbinentriebwerke
DE19859210A1 (de) Brennstoff-Luft-Mischanordnung für Verbrennungsvorrichtungen
DE112021000904T5 (de) Brenneranordnung, gasturbinen-brennkammer und gasturbine
DE102019217830A1 (de) Brennkammer und gasturbine
DE102020212361B4 (de) Gasturbinenverbrennungsvorrichtung
EP2161502A1 (fr) Brûleur à prémélange pour un combustible pauvre et riche
DE2116429A1 (de) Brennkammer fur Gasturbinenmaschinen

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20051110

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE ES GB IT LI PL

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

DAX Request for extension of the european patent (deleted)
RBV Designated contracting states (corrected)

Designated state(s): CH DE ES GB IT LI PL

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE ES GB IT LI PL

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20070822

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG

Ref country code: CH

Ref legal event code: EP

REF Corresponds to:

Ref document number: 502004004752

Country of ref document: DE

Date of ref document: 20071004

Kind code of ref document: P

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2288687

Country of ref document: ES

Kind code of ref document: T3

REG Reference to a national code

Ref country code: PL

Ref legal event code: T3

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20080526

REG Reference to a national code

Ref country code: CH

Ref legal event code: PCAR

Free format text: SIEMENS SCHWEIZ AG;INTELLECTUAL PROPERTY FREILAGERSTRASSE 40;8047 ZUERICH (CH)

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20120626

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20130610

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: PL

Payment date: 20130522

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20130711

Year of fee payment: 10

Ref country code: CH

Payment date: 20130909

Year of fee payment: 10

Ref country code: DE

Payment date: 20130819

Year of fee payment: 10

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130616

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502004004752

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20140616

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502004004752

Country of ref document: DE

Effective date: 20150101

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140630

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140630

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150101

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140616

REG Reference to a national code

Ref country code: PL

Ref legal event code: LAPE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140616

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20160201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140617