EP1423647B1 - Dispositif a chambre de combustion - Google Patents

Dispositif a chambre de combustion Download PDF

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Publication number
EP1423647B1
EP1423647B1 EP02767441A EP02767441A EP1423647B1 EP 1423647 B1 EP1423647 B1 EP 1423647B1 EP 02767441 A EP02767441 A EP 02767441A EP 02767441 A EP02767441 A EP 02767441A EP 1423647 B1 EP1423647 B1 EP 1423647B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
turbine
individual
chamber arrangement
combustion chambers
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 - Fee Related
Application number
EP02767441A
Other languages
German (de)
English (en)
Other versions
EP1423647A1 (fr
Inventor
Peter Tiemann
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
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP02767441A priority Critical patent/EP1423647B1/fr
Publication of EP1423647A1 publication Critical patent/EP1423647A1/fr
Application granted granted Critical
Publication of EP1423647B1 publication Critical patent/EP1423647B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F23R3/42—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
    • 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
    • F01D25/14—Casings modified therefor
    • 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
    • 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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Definitions

  • the invention relates to a combustion chamber arrangement for a gas turbine with a plurality of opening in a common annular gap leading into a turbine chamber single combustion chambers, wherein the individual combustion chambers are upstream burner, which are connected to the individual combustion chambers through an outer housing.
  • the invention further relates to a gas turbine with such a combustion chamber arrangement.
  • Such combustion chamber arrangements for gas turbines are known in the art.
  • a mixture of an oxygen-containing fuel gas and a fuel ignited in the burners is burned in the combustion chambers and the expanding hot gases are diverted through the transition sections of the individual combustion chambers in the direction of the turbine chamber and the arrangement of vanes and blades therein.
  • the hot gas flows of circular cross-section generated in the usually circular-cylindrical constructed input sections of the individual combustion chambers are transferred through the transition sections into a hot gas flow with a circular-segment-shaped cross-section and finally combined to form a circular hot gas flow. This enters through the annular gap in the turbine chamber and drives the blades of the gas turbine.
  • Cooling fluid flows openly past the individual combustion chambers and causes a cooling effect.
  • the individual combustion chambers are designed with a simple wall, the cooling fluid flow is not directed and defined guided, resulting in an overall lower cooling efficiency.
  • such a design of the individual combustion chambers is structurally simpler and requires less effort.
  • the present invention seeks to further develop a combustion chamber arrangement of the type mentioned in that with structurally simple individual combustion chambers, the cooling efficiency can be significantly increased.
  • a cooling fluid can flow and cause a more effective convective cooling in this area due to the defined flow channel.
  • the single combustion chamber itself remains unchanged in its structure, a complication of the construction of the single combustion chamber itself is not required. In this way, the quasi closed cooled region of the single combustion chamber is extended into the interior of the turbine outer housing in the direction of the turbine space, the cooling efficiency is noticeably improved.
  • At least one tongue-like extension is formed on the neck, along a tangential to the annular gap, flattened side of the transition section of the single combustion chamber, leaving an intermediate space extend this.
  • the nozzle at the point where he collides with a nozzle for an adjacent single combustion chamber recesses the one substantially form dense transition to corresponding recesses of the adjacent nozzle.
  • the nozzle according to an advantageous embodiment of the invention may be formed closed in the circumferential direction of the single combustion chamber, so that over the entire peripheral region of the single combustion chamber in the section in which the nozzle according to the invention protrudes into the interior of the outer casing of the gas turbine quasi closed cooled.
  • the single combustion chamber is composed of a substantially cylindrically shaped, the burner downstream input section and a transition in a circular ring sector transition section, wherein the nozzle surrounds at least the input portion partially.
  • the inlet section is a thermally highly stressed element of the individual combustion chamber, so that the possibility of a quasi-closed cooling, which is provided in this area due to the neck provided according to the invention, results in a considerable improvement in the cooling of the Single combustion chamber with comparatively lower cost of cooling fluid represents.
  • a low cost of cooling fluid increases the overall cost of the gas turbine, and in cases where the cooling fluid is used simultaneously as fuel gas, the efficiency of the gas turbine is also increased.
  • the nozzle has a circular cross-sectional area and is arranged concentrically around the nikzylindrisch formed input section. This results in a uniform gap in the circumferential direction of the input section, which allows a uniform distribution of the cooling fluid flow and thus a uniform cooling in this area.
  • a gas turbine with a combustion chamber arrangement according to the previous embodiments is also the subject of the invention.
  • FIG. 1 shows a section of a gas turbine with a combustion chamber arrangement 1 according to the invention in a sectional view.
  • the combustion chamber assembly 1 is composed of a plurality of individual combustion chambers 3, which are arranged in a coronary manner and open into a common annular gap 13.
  • the annular gap 13 in turn opens into a turbine chamber 2, in which schematically indicated guide vanes and rotor blades of the turbine are located.
  • the individual combustion chambers 3 each burner 6 are connected upstream. These serve to ignite a mixture of an oxygen-containing fuel gas and a fuel, which burns in the individual combustion chambers 3 on.
  • the individual combustion chambers 3 are made up of an inlet section 4 adjoining the burner 6 and a transition section 5 which leads the inlet section 4 in the direction of the annular gap 13.
  • the burners 6 are connected to the individual combustion chambers 3 through a turbine outer housing 7. Starting from the turbine outer housing 7 in the direction of the turbine chamber 2, a nozzle 8 can be recognized, which extends concentrically around the circular cylindrical input section 4 of the single combustion chamber 3. Between the nozzle 8 and the input portion 4 of the single combustion chamber 3 while a gap space 9 is left, which can be traversed by a cooling fluid.
  • the ribs 10 are formed in the illustrated embodiment of the single combustion chamber 3, they However, they can also be formed on the neck 8 and extend in the direction of the single combustion chamber 3.
  • a recess 11 can be seen on the side of the nozzle 8, which is followed by an adjacent nozzle adjacent a single combustion chamber.
  • the individual combustion chambers are each arranged at an angle to one another.
  • the distance between the individual combustion chambers is reduced starting from the burner 6 in the direction of the annular gap 13, so that the cylindrical nozzle 8 abut each other in the direction of the annular gap 13 from a certain extent.
  • the recesses 11 are arranged in order to be able to extend the stubs 8 further in the direction of the annular gap 13 inwards.
  • adjacent sockets 8 abut each other and can be connected to each other for sealing, for example, welded, be.
  • the present invention arranged nozzle 8 form with its gap 9 a flow channel for a cooling fluid.
  • the quasi-closed in the flow channel guided cooling fluid due to the defined flow channel effectively contributes to a convective cooling of the individual combustion chambers 3 in the area covered by the nozzle 8 area.
  • tongue-like extensions 12a and 12b are further visible, which are guided while leaving a gap along the transition section 5 of the single combustion chamber 3.
  • These tongue-like extensions 12a and 12b represent an advantageous development of the invention, but are optional. They lead to a further enlargement of the quasi closed cooled region of the single combustion chamber 3 and thus to a further improvement of the cooling efficiency.
  • basic version of a combustion chamber arrangement according to the invention can be realized without the tongue-like extensions 12a and 12b only with the nozzle 8.
  • FIGS. 2 and 3 cutouts from combustion chamber arrangements designed according to the invention are shown in perspective from different viewing directions.
  • FIGS. 2 and 3 cutouts from combustion chamber arrangements designed according to the invention are shown in perspective from different viewing directions.
  • the different design variants with and without tongue-like extensions 12a and 12b only some of the single combustion chamber 3 at least in the input section 4 surrounding nozzle 8 with the tongue-like extension 12a and 12b shown.
  • the course of the flow 14 of a coolant fluid from the openly cooled region in the direction of the gaps under the tongue-like extensions 12a and subsequently below the connecting pieces 8 is shown in FIG.
  • the tongue-like extensions 12a and 12b taper in the direction of the outlet leading into the gap from the transition section 5 of the individual combustion chambers 3. This ensures a sufficiently large inlet surface for the cooling fluid flow.
  • combustion chamber arrangement 1 according to the invention a virtually closed-cooled region of the individual combustion chambers is created, in which cooling of the individual combustion chambers is possible with high efficiency.
  • the individual combustion chambers continue to be of simple construction, a complex double-walled design of the individual combustion chambers is not required.
  • the invention thus provides a simple means of providing a simple combustion chamber arrangement with the possibility of highly efficient cooling.

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 dispositif à chambre de combustion (1) pour turbine à gaz, comprenant une pluralité de chambres à combustion individuelles (3) débouchant dans une fente annulaire commune (13) aboutissant dans un espace (2) de la turbine, des brûleurs (6), montés en amont desdites chambres de combustion (3), étant connectés avec celles-ci à travers la carcasse (7) de la turbine. L'invention a pour but de perfectionner le dispositif précité de manière à augmenter considérablement, par des modifications constructives simples des chambres de combustion individuelles, l'efficacité du refroidissement. A cet effet, l'invention est caractérisée en ce qu'au moins une tubulure (8) s'étendant radialement en direction de l'espace (2) de la turbine est disposée sur un côté tourné vers ledit espace (2), et en ce que cette tubulure entoure au moins partiellement une section d'au moins une chambre de combustion individuelle (3), tout en ménageant un espace intercalaire (9).

Claims (8)

  1. Agencement de chambres de combustion pour une turbine à gaz, ayant une pluralité de chambres de combustion individuelles (2) débouchant dans un interstice annulaire commun (13) passant dans un compartiment de turbine (2), des brûleurs (6) qui sont reliés avec les chambres de combustion individuelles (3) en traversant un carter extérieur de turbine (7) étant montés en amont des chambres de combustion individuelles (3), une tubulure (8) qui entoure au moins partiellement un tronçon d'au moins l'une des chambres de combustion individuelles (3), en laissant libre un espace en forme d'interstice (9), et qui s'étend dans le sens radial en direction du compartiment de turbine(2), étant disposée sur un côté du carter extérieur de turbine (7) qui fait face au compartiment de turbine (2),
    caractérisé par un prolongement (12a, 12b) du type d'une languette, qui est constitué sur la tubulure (8), qui dépasse d'un côté, aplati et tangentiel par rapport à l'interstice annulaire, du tronçon de transition (5), en laissant libre un espace en forme d'interstice.
  2. Agencement de chambres de combustion suivant la revendication 1,
    caractérisé en ce que la au moins une tubulure (8) est conçue sous forme fermée, dans le sens périphérique de la chambre de combustion individuelle (3).
  3. Agencement de chambres de combustion suivant l'une quelconque des revendications précédentes, caractérisé en ce que la chambre de combustion individuelle (3) est composée d'un tronçon d'entrée (4) de forme sensiblement cylindrique, monté en aval du brûleur (6) et d'un tronçon de transition (5) recouvrant une section transversale en forme d'un secteur en anneau de cercle (5), la tubulure (8) entourant au moins partiellement le tronçon d'entrée (4).
  4. Agencement de chambres de combustion suivant la revendication 3,
    caractérisé en ce que le tronçon d'entrée (4) est conçu sous la forme d'un cylindre circulaire et en ce que la tubulure (8) présente une surface de section transversale circulaire et en ce qu'elle est disposée de façon concentrique autour du tronçon d'entrée (4).
  5. Agencement de chambres de combustion suivant la revendication 1,
    caractérisé en ce que le prolongement du type d'une languette (12a, 12b) est constitué de façon à se rétrécir en direction de l'interstice annulaire (13).
  6. Agencement de chambres de combustion suivant l'une quelconque des revendications 1 à 5,
    caractérisé en ce que dans la zone où elles rencontrent des tubulures (8) disposées autour de chambres de combustion voisines (3), les tubulures (8) comportent des évidements latéraux (11), le long desquels les tubulures voisines (8) s'appliquent étroitement l'une contre l'autre.
  7. Agencement de chambre de combustion suivant la revendication 6, caractérisé en ce que les tubulures voisines sont reliées entre elles le long des bords des évidements (11).
  8. Turbine à gaz, caractérisée par un agencement de chambres de combustion (1) suivant l'une quelconque des revendications 1 à 7.
EP02767441A 2001-09-03 2002-08-27 Dispositif a chambre de combustion Expired - Fee Related EP1423647B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP02767441A EP1423647B1 (fr) 2001-09-03 2002-08-27 Dispositif a chambre de combustion

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP01121089A EP1288574A1 (fr) 2001-09-03 2001-09-03 Agencement de chambre de combustion
EP01121089 2001-09-03
PCT/EP2002/009556 WO2003021149A1 (fr) 2001-09-03 2002-08-27 Dispositif a chambre de combustion
EP02767441A EP1423647B1 (fr) 2001-09-03 2002-08-27 Dispositif a chambre de combustion

Publications (2)

Publication Number Publication Date
EP1423647A1 EP1423647A1 (fr) 2004-06-02
EP1423647B1 true EP1423647B1 (fr) 2006-07-26

Family

ID=8178516

Family Applications (2)

Application Number Title Priority Date Filing Date
EP01121089A Withdrawn EP1288574A1 (fr) 2001-09-03 2001-09-03 Agencement de chambre de combustion
EP02767441A Expired - Fee Related EP1423647B1 (fr) 2001-09-03 2002-08-27 Dispositif a chambre de combustion

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP01121089A Withdrawn EP1288574A1 (fr) 2001-09-03 2001-09-03 Agencement de chambre de combustion

Country Status (6)

Country Link
US (1) US6968672B2 (fr)
EP (2) EP1288574A1 (fr)
JP (1) JP2005502020A (fr)
CN (1) CN1537212A (fr)
DE (1) DE50207662D1 (fr)
WO (1) WO2003021149A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7155800B2 (en) 2005-02-24 2007-01-02 General Electric Company Automated seal strip assembly method and apparatus for rotary machines
US7082766B1 (en) * 2005-03-02 2006-08-01 General Electric Company One-piece can combustor
EP2211023A1 (fr) * 2009-01-21 2010-07-28 Siemens Aktiengesellschaft Distributeur pour turbomachine avec structure support d'aubes directrices segmentée
US8201412B2 (en) * 2010-09-13 2012-06-19 General Electric Company Apparatus and method for cooling a combustor
DE102011007562A1 (de) * 2011-04-18 2012-10-18 Man Diesel & Turbo Se Brennkammergehäuse und damit ausgerüstete Gasturbine
US8650852B2 (en) * 2011-07-05 2014-02-18 General Electric Company Support assembly for transition duct in turbine system

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3169367A (en) * 1963-07-18 1965-02-16 Westinghouse Electric Corp Combustion apparatus
US3840332A (en) * 1973-03-05 1974-10-08 Stone Platt Crawley Ltd Combustion chambers
GB1492049A (en) * 1974-12-07 1977-11-16 Rolls Royce Combustion equipment for gas turbine engines
US4008568A (en) * 1976-03-01 1977-02-22 General Motors Corporation Combustor support
US4297842A (en) * 1980-01-21 1981-11-03 General Electric Company NOx suppressant stationary gas turbine combustor
JPS59229114A (ja) * 1983-06-08 1984-12-22 Hitachi Ltd ガスタ−ビン用燃焼器
US4719748A (en) * 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
US4794753A (en) * 1987-01-06 1989-01-03 General Electric Company Pressurized air support for catalytic reactor
GB9220937D0 (en) * 1992-10-06 1992-11-18 Rolls Royce Plc Gas turbine engine combustor
US5323600A (en) * 1993-08-03 1994-06-28 General Electric Company Liner stop assembly for a combustor
FR2710968B1 (fr) * 1993-10-06 1995-11-03 Snecma Chambre de combustion à double paroi.
US6182451B1 (en) * 1994-09-14 2001-02-06 Alliedsignal Inc. Gas turbine combustor waving ceramic combustor cans and an annular metallic combustor
US5737913A (en) * 1996-10-18 1998-04-14 The United States Of America As Represented By The Secretary Of The Air Force Self-aligning quick release engine case assembly
JP3110338B2 (ja) * 1997-02-12 2000-11-20 東北電力株式会社 燃焼器の蒸気による冷却構造
GB2328011A (en) * 1997-08-05 1999-02-10 Europ Gas Turbines Ltd Combustor for gas or liquid fuelled turbine
DE19801626B4 (de) * 1998-01-17 2010-08-12 Robert Bosch Gmbh Diagnose eines NOx-Speicherkatalysators beim Betrieb von Verbrennungsmotoren
US6098397A (en) * 1998-06-08 2000-08-08 Caterpillar Inc. Combustor for a low-emissions gas turbine engine
US6354071B2 (en) * 1998-09-25 2002-03-12 General Electric Company Measurement method for detecting and quantifying combustor dynamic pressures
US6216442B1 (en) * 1999-10-05 2001-04-17 General Electric Co. Supports for connecting a flow sleeve and a liner in a gas turbine combustor

Also Published As

Publication number Publication date
US20040237500A1 (en) 2004-12-02
EP1423647A1 (fr) 2004-06-02
JP2005502020A (ja) 2005-01-20
WO2003021149A1 (fr) 2003-03-13
DE50207662D1 (de) 2006-09-07
EP1288574A1 (fr) 2003-03-05
US6968672B2 (en) 2005-11-29
CN1537212A (zh) 2004-10-13

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