EP1934523B1 - Chambre de combustion et turbine à gaz - Google Patents

Chambre de combustion et turbine à gaz Download PDF

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Publication number
EP1934523B1
EP1934523B1 EP06793722.7A EP06793722A EP1934523B1 EP 1934523 B1 EP1934523 B1 EP 1934523B1 EP 06793722 A EP06793722 A EP 06793722A EP 1934523 B1 EP1934523 B1 EP 1934523B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
burner
wall
insert
burner insert
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.)
Ceased
Application number
EP06793722.7A
Other languages
German (de)
English (en)
Other versions
EP1934523A1 (fr
Inventor
Uwe Gruschka
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
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 EP06793722.7A priority Critical patent/EP1934523B1/fr
Publication of EP1934523A1 publication Critical patent/EP1934523A1/fr
Application granted granted Critical
Publication of EP1934523B1 publication Critical patent/EP1934523B1/fr
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/78—Cooling burner parts
    • 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 present invention relates to a combustion chamber, in particular a combustion chamber for a gas turbine plant, comprising a burner and a burner insert surrounding the burner while leaving a gap open towards the interior of the combustion chamber.
  • a gas turbine plant with such a combustion chamber.
  • a gas turbine plant is a turbomachine that essentially comprises a compressor section, a turbine section and a burner section with one or more combustion chambers arranged between the compressor section and the turbine section.
  • ambient air is sucked through the compressor and compressed to an elevated pressure.
  • the compressed air is supplied to the burner section, where it is burned by means of a burner in a combustion chamber.
  • the combustion exhaust gas which is hot due to combustion and is under high pressure, is finally supplied as a working medium to the turbine section, where it relaxes and cools under power, converting the energy of the working fluid into mechanical work.
  • the energy converted in the turbine section in mechanical work serves on the one hand to drive the compressor and on the other hand to drive a consumer, for example a generator for generating electricity.
  • premix combustion In modern gas turbine plants mostly the so-called premix combustion is used.
  • premix combustion the fuel is first mixed with an oxidant, typically air, before the mixture is ignited.
  • pilot fuel mass flow In the premix combustion often comes a separate fuel mass flow used, which is used to stabilize the flame use and is referred to as pilot fuel mass flow.
  • the pilot fuel mass flow becomes fed via a separate from the main fuel supply system. It serves to protect the flame from instabilities due to the thermoacoustic behavior of the combustion.
  • pilot mixed premix combustion Premix combustion using a pilot gas stream is also called pilot mixed premix combustion.
  • piloted premix combustion the NO x emission of the combustion system depends on the amount of pilot mass fuel flow supplied. The lower the pilot fuel mass flow, the lower the NO x emission.
  • a combustion chamber with a burner designed for piloted premix combustion is known, for example, in US Pat US 2005/0016178 A1 described.
  • the burner is surrounded by a burner insert, wherein between the burner insert and the burner to the combustion chamber interior open annular gap is present.
  • the combustion chamber insert comprises a carrier as well as a burner insert wall arranged upstream of the carrier towards the interior of the combustion chamber and simultaneously forming the combustion chamber wall in the region of the burner.
  • a cooling air channel is formed between the burner insert wall and the carrier, which is supplied from the outside of the combustion chamber with cooling air. This cooling air channel is sealed against the annular gap between the burner insert and the burner.
  • At the end of the burner insert wall remote from the burner there is also an opening to the interior of the combustion chamber, via which the cooling air flowing through the cooling air passage is discharged into the combustion chamber interior.
  • Another object of the present invention is to provide an improved gas turbine plant.
  • the first object is achieved by a combustion chamber with a burner and a burner insert surrounding the burner according to claim 1.
  • the second object by a gas turbine plant according to claim 8.
  • a combustion chamber according to the invention is equipped with a burner and a burner insert surrounding the burner.
  • the burner may be suitable in particular for pilot-operated premix combustion. Between the burner and the burner insert, a gap open towards the interior of the combustion chamber is left.
  • the combustion chamber insert comprises a carrier and a carrier insert wall which precedes the carrier toward the combustion chamber interior and between which a flow channel communicating with a cooling fluid source is formed. The flow channel opens into the gap between the burner and the burner insert and is otherwise sealed against the combustion chamber interior.
  • the inventive design of the combustion chamber makes it possible to cool the burner insert wall, which also forms the combustion chamber wall usually used cooling fluid in the gap between the burner and the burner insert. In this way, an introduction of cooling fluid, usually cooling air, take place directly at the burner outlet.
  • cooling fluid usually cooling air
  • By introducing cooling fluid in the immediate vicinity of the burner outlet into the combustion chamber it is possible to achieve an improvement in the thermoacoustic behavior of the combustion exhaust gases in the combustion chamber. Due to the improved thermoacoustic behavior can be made a reduction in the pilot gas quantity, resulting in a reduction in NO x emissions follows.
  • the burner insert wall is usually fastened by means of a rib engaging in a groove of the carrier rib in the region of the flow channel on the carrier.
  • the rib in this case has at least one passage opening enabling the passage of cooling fluid, for example at least one bore.
  • the carrier has cooling fluid channels, which communicate directly or indirectly with the cooling fluid source and open into the flow channel.
  • cooling fluid channels which communicate directly or indirectly with the cooling fluid source and open into the flow channel.
  • the combustion chamber according to the invention can in particular be designed as an axially symmetrical annular combustion chamber with a number of burners distributed around the axis of symmetry and at least one burner insert.
  • the burner insert wall of a burner insert has at least one abutting edge on which it adjoins a abutting edge of an adjacent burner insert or on a combustion chamber wall.
  • a seal is then present, which seals the burner insert wall against the combustion chamber interior. In this way you can prevent that from flowing through the flow channel flowing cooling fluid instead through the gap between the burner and the burner insert flows through gaps between adjacent burner inserts or between a burner insert and the combustion chamber wall into the combustion chamber.
  • a gas turbine plant according to the invention is equipped with a combustion chamber according to the invention.
  • FIG. 1 A section of a combustion chamber according to the invention is in FIG. 1 shown in a sectional view.
  • a burner 1 a burner insert 3, which annularly surrounds the burner 1, and to recognize a part of the combustion chamber wall 5.
  • the combustion chamber is arranged in a Brennschplenum 4 and extends annularly around a turbine shaft (not shown).
  • the burner 1 is inserted into a receptacle of the burner insert 3.
  • the burner insert 3 adjoins the combustion chamber wall 5 and closes off the combustion chamber.
  • the burner insert 3 comprises a carrier 7, which is designed as a grooved ring: In this run one or more annular grooves around the burner 1 around, can be supplied to the burner 1 by the cooling air. For better clarity, the grooves are not shown.
  • the grooved ring 7 upstream of the combustion chamber interior 2 towards a burner insert wall 9 is present, which at the same time represents the burner 1 surrounding the end wall of the combustion chamber 1.
  • the burner insert wall 9 has a circumferential web 23, with which the wall is inserted into a groove 21 of the grooved ring 7 and held there. Through bores 11, 15 in the grooved ring 7, the side of the burner insert wall 9 facing away from the combustion chamber interior 2 can be blown with cooling air in order to effect impingement cooling.
  • FIG. 3 The grooved ring 7, the burner insert wall 9 and a section of the combustion chamber wall 5 and a section of the burner 1 are in FIG. 3 shown enlarged. Between the U-ring 7 and the burner insert wall 9, a flow channel 13 is formed, which is supplied from the Brennschplenum 4 fro cooling air as cooling fluid. In this sense, combustor plenum 4 may be considered as a source of cooling fluid.
  • the flow paths of the cooling air are in FIG. 3 indicated by arrows.
  • a seal 19 is arranged between the abutting edge and the combustion chamber wall 5.
  • the seal is preferably flexible in order to compensate for thermal expansions. It can e.g. be made as metal.
  • the gap between the burner 1 and the burner insert 3 is sealed by a serving as a seal piston ring 31.
  • the cooling air used for cooling the burner insert wall 9 flows into the combustion chamber directly next to the burner outlet 33 through an annular gap 29 and is fed to the combustion process. This improves the thermoacoustic behavior of the combustion chamber and thereby enables a reduction of the supplied pilot fuel quantity and thus to a reduction of the NO x emissions.
  • FIG. 2 A top view of the burner insert 3 and the burner 1 seen from the combustion chamber interior is in FIG. 2 shown. Arrows indicate the flow paths of the cooling air along the combustion chamber insert wall 9.
  • combustion chamber In the center of the burner insert 3, the burner wall 33 surrounding the burner opening 27 can be seen. Between the burner insert wall 9 and the combustion wall 27 is the annular gap 29 through which the cooling air used for cooling the burner insert wall 9 flows into the combustion chamber interior 2.
  • combustion chamber In the FIG. 2 illustrated combustion chamber is an annular combustion chamber, which is arranged axially symmetrically around a turbine rotor.
  • the radially outer combustion chamber wall 5A and the radially inner combustion chamber wall 5B can be seen.
  • seals 19A and 19B are provided, which seal the flow channel of the combustion chamber insert 3 against the combustion chamber interior 2.
  • a separate burner insert 3 is present for each burner 1.
  • the burner inserts 3 adjoin one another in the circumferential direction of the combustion chamber. Gaps between opposing abutting edges 17C, 17D of burner insert walls 9 of adjacent burner inserts 3 are also sealed with seals 19C, 19D against the combustion chamber interior to prevent leakage of cooling air through these gaps.
  • seals 19C, 19D against the combustion chamber interior to prevent leakage of cooling air through these gaps.
  • the air mass flow supplied to the combustion chamber interior 2 through the flow channel 13 corresponds to only a few percent of the air mass flow fed through the burner 1.
  • the air mass flow supplied through the flow channel 13 is less than about 5% of the air mass flow supplied by the burner 1.
  • combustion chamber can also be designed as an approximately cylindrical combustion chamber with at least one burner and at least one burner insert on the end face of the cylinder.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Claims (8)

  1. Chambre de combustion, comprenant un brûleur ( 1 ) et un insert ( 3 ) de brûleur, qui entoure le brûleur ( 1 ) en laissant un intervalle ( 29 ) ouvert en direction de l'intérieur ( 2 ) de la chambre de combustion et qui comprend un support ( 7 ) et une paroi ( 9 ) d'insert de brûleur posée avant le support ( 7 ) par rapport à l'intérieur ( 2 ) de la chambre de combustion, un canal ( 13 ) d'écoulement en communication avec une source ( 4 ) de fluide de refroidissement étant formé entre le support ( 7 ) et la paroi ( 9 ) de l'insert de brûleur, caractérisée en ce que le canal ( 13 ) d'écoulement débouche dans l'intervalle ( 29 ) entre le brûleur ( 1 ) et l'insert ( 3 ) de brûleur et pour le reste est rendu étanche vis-à-vis de l'intérieur ( 2 ) de la chambre de combustion.
  2. Chambre de combustion suivant la revendication 1, caractérisée en ce que la paroi ( 9 ) de l'insert de brûleur est fixée au support ( 7 ) au moyen d'une nervure ( 23 ) pénétrant dans la région du canal ( 13 ) d'écoulement dans une rainure ( 21 ) du support ( 7 ) et la nervure ( 23 ) a au moins une ouverture ( 25 ) de passage permettant un passage du fluide de refroidissement.
  3. Chambre de combustion suivant la revendication 2, caractérisée en ce que la au moins une ouverture de passage est conformée sous la forme d'un trou ( 25 ) dans la nervure.
  4. Chambre de combustion suivant l'une des revendications précédentes,
    caractérisée en ce que le support ( 7 ) a des canaux ( 11, 15 ) pour du fluide de refroidissement, qui sont en communication indirectement ou directement avec la source ( 4 ) de fluide de refroidissement et qui débouchent dans le canal ( 13 ) d'écoulement.
  5. Chambre de combustion suivant l'une des revendications précédentes,
    caractérisée en ce qu'il y a, entre le support ( 7 ) et le brûleur ( 1 ), un joint ( 31 ) rendant l'intervalle ( 29 ) étanche vis-à-vis d'un plénum de la chambre de combustion.
  6. Chambre de combustion suivant l'une des revendications précédentes,
    caractérisée par sa conformation sous la forme d'une chambre de combustion annulaire à symétrie axiale, ayant un certain nombre de brûleurs ( 1 ) répartis autour de l'axe de symétrie et au moins un insert ( 3 ) de brûleur.
  7. Chambre de combustion suivant l'une des revendications précédentes,
    caractérisée en ce que la paroi ( 9 ) d'un insert ( 3 ) de brûleur a au moins un rebord ( 17 ), où la paroi ( 9 ) d'insert de brûleur est voisine d'un rebord ( 17 ) d'un insert ( 3 ) de brûleur voisin ou d'une paroi ( 5 ) de la chambre de combustion, et en ce que, entre les rebords ( 17 ) d'insert ( 3 ) de brûleur voisins et/ou entre le rebord ( 17 ) et la paroi ( 5 ) de la chambre de combustion, il y a un joint ( 19 ), qui rend étanche la paroi ( 9 ) de l'insert de brûleur vis-à-vis de l'intérieur ( 2 ) de la chambre de combustion.
  8. Installation de turbine à gaz ayant une chambre de combustion suivant l'une des revendications précédentes.
EP06793722.7A 2005-09-27 2006-09-21 Chambre de combustion et turbine à gaz Ceased EP1934523B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06793722.7A EP1934523B1 (fr) 2005-09-27 2006-09-21 Chambre de combustion et turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05021085A EP1767855A1 (fr) 2005-09-27 2005-09-27 Chambre de combustion et turbine à gaz
PCT/EP2006/066602 WO2007036486A1 (fr) 2005-09-27 2006-09-21 Chambre a combustion et installation de turbine a gaz
EP06793722.7A EP1934523B1 (fr) 2005-09-27 2006-09-21 Chambre de combustion et turbine à gaz

Publications (2)

Publication Number Publication Date
EP1934523A1 EP1934523A1 (fr) 2008-06-25
EP1934523B1 true EP1934523B1 (fr) 2014-10-29

Family

ID=35636740

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05021085A Withdrawn EP1767855A1 (fr) 2005-09-27 2005-09-27 Chambre de combustion et turbine à gaz
EP06793722.7A Ceased EP1934523B1 (fr) 2005-09-27 2006-09-21 Chambre de combustion et turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP05021085A Withdrawn EP1767855A1 (fr) 2005-09-27 2005-09-27 Chambre de combustion et turbine à gaz

Country Status (3)

Country Link
US (1) US8393161B2 (fr)
EP (2) EP1767855A1 (fr)
WO (1) WO2007036486A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019217983A1 (de) * 2019-11-21 2021-05-27 Siemens Aktiengesellschaft Brennereinsatz, Verfahren zu dessen Herstellung sowie Verwendung eines solchen Brennereinsatzes

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
EP2182285A1 (fr) 2008-10-29 2010-05-05 Siemens Aktiengesellschaft Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
EP2354661B1 (fr) * 2010-02-04 2018-04-11 General Electric Technology GmbH Dispositif de combustion pour turbine à gaz
GB201107090D0 (en) * 2011-04-28 2011-06-08 Rolls Royce Plc A head part of an annular combustion chamber
EP2522909B1 (fr) * 2011-05-12 2015-04-08 Siemens Aktiengesellschaft Turbine à gaz avec brûleur et procédé de réglage d'une turbine à gaz dotée d'un tel brûleur
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
US11774093B2 (en) * 2020-04-08 2023-10-03 General Electric Company Burner cooling structures

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4322945A (en) * 1980-04-02 1982-04-06 United Technologies Corporation Fuel nozzle guide heat shield for a gas turbine engine
DE19508111A1 (de) * 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Hitzeschild-Anordnung für eine Gasturbinen-Brennkammer
ITMI991207A1 (it) * 1999-05-31 2000-12-01 Nuovo Pignone Spa Camera di combustione per turbine a gas
US6314739B1 (en) * 2000-01-13 2001-11-13 General Electric Company Brazeless combustor dome assembly
US6546733B2 (en) * 2001-06-28 2003-04-15 General Electric Company Methods and systems for cooling gas turbine engine combustors
US6581386B2 (en) * 2001-09-29 2003-06-24 General Electric Company Threaded combustor baffle
US7080515B2 (en) 2002-12-23 2006-07-25 Siemens Westinghouse Power Corporation Gas turbine can annular combustor

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019217983A1 (de) * 2019-11-21 2021-05-27 Siemens Aktiengesellschaft Brennereinsatz, Verfahren zu dessen Herstellung sowie Verwendung eines solchen Brennereinsatzes
WO2021099055A1 (fr) 2019-11-21 2021-05-27 Siemens Energy Global GmbH & Co. KG Pièce rapportée de brûleur, procédé de fabrication associé et utilisation dudit type de pièce rapportée de brûleur

Also Published As

Publication number Publication date
EP1767855A1 (fr) 2007-03-28
US8393161B2 (en) 2013-03-12
US20090133378A1 (en) 2009-05-28
EP1934523A1 (fr) 2008-06-25
WO2007036486A1 (fr) 2007-04-05

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