EP0590338A1 - Chambre de combustion pour turbines à gaz - Google Patents

Chambre de combustion pour turbines à gaz Download PDF

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Publication number
EP0590338A1
EP0590338A1 EP93114040A EP93114040A EP0590338A1 EP 0590338 A1 EP0590338 A1 EP 0590338A1 EP 93114040 A EP93114040 A EP 93114040A EP 93114040 A EP93114040 A EP 93114040A EP 0590338 A1 EP0590338 A1 EP 0590338A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
combustion chamber
convective
turbine combustion
cooling
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.)
Withdrawn
Application number
EP93114040A
Other languages
German (de)
English (en)
Inventor
Rolf Dr. Althaus
Burkhard Schulte-Wrening
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0590338A1 publication Critical patent/EP0590338A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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

Definitions

  • the invention relates to a gas turbine combustor in which combinations of convective heat transfer mechanisms are used for cooling, the basic principle of which is the heat dissipation by flow.
  • Such gas turbine combustors are known.
  • the to implement the above The basic principle of the necessary cooling air speed is caused by a drop in pressure. Due to the friction effects in the cooling channels, part of the kinetic energy of the cooling medium is irreversibly converted into heat, thereby reducing the total pressure.
  • the invention tries to avoid all these disadvantages. It is based on the task of designing the transition from the convective cooling duct to the plenum of the burner in a gas turbine combustion chamber in such a way that the total pressure loss in the overall system is reduced. Furthermore, it is based on the additional task of creating an increased design scope for convective cooling measures of the combustion chamber walls, so that the efficiency of the gas turbine is improved compared to the prior art.
  • Fig. 1 part of the gas turbine combustor is shown. It consists of the outer jacket 1, which has to absorb the pressure forces and the inner jacket 2, which is directly exposed to the hot combustion gases. Between the outer jacket 1 and the inner jacket 2, the cooling air flows, which keeps the inner jacket 2 at the temperature necessary for strength and cools it slightly.
  • the fuel nozzle 3 atomizes the fuel under pressure.
  • the transition from the convective cooling duct 4 to the plenum in front of the environmentally friendly burner 5 is formed by the small diffuser 6, which serves to delay the cooling air flow and to recover part of the pressure.
  • the small diffuser 6 has a channel height of 10 mm at the end of the cooling section.
  • the usual diffuser design diagrams for optimal pressure recovery result in an opening angle of 4.3 ° and a length of 40 mm. These sizes can easily be realized in a conventional combustion chamber design.
  • the advantage of the invention is that, compared to the prior art, the total pressure loss in the overall system is reduced. This leads to an improved efficiency of the gas turbine plant. No cooling measures are required in the extended room, since there is no heat input from the combustion.

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)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
EP93114040A 1992-09-28 1993-09-02 Chambre de combustion pour turbines à gaz Withdrawn EP0590338A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19924232442 DE4232442A1 (de) 1992-09-28 1992-09-28 Gasturbinenbrennkammer
DE4232442 1992-09-28

Publications (1)

Publication Number Publication Date
EP0590338A1 true EP0590338A1 (fr) 1994-04-06

Family

ID=6469012

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93114040A Withdrawn EP0590338A1 (fr) 1992-09-28 1993-09-02 Chambre de combustion pour turbines à gaz

Country Status (3)

Country Link
EP (1) EP0590338A1 (fr)
JP (1) JPH06221555A (fr)
DE (1) DE4232442A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH699309A1 (de) * 2008-08-14 2010-02-15 Alstom Technology Ltd Thermische maschine mit luftgekühlter, ringförmiger brennkammer.

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19523094A1 (de) * 1995-06-26 1997-01-02 Abb Management Ag Brennkammer
DE19720786A1 (de) * 1997-05-17 1998-11-19 Abb Research Ltd Brennkammer

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2482E (fr) * 1902-04-30 1904-04-27 Gaston Charles Emile De Bonnec Système de turbo-moteur à combustion continue
US4288980A (en) * 1979-06-20 1981-09-15 Brown Boveri Turbomachinery, Inc. Combustor for use with gas turbines
JPS60185025A (ja) * 1984-03-02 1985-09-20 Hitachi Ltd 再生サイクルガスタ−ビン用燃焼器ライナ
EP0491625A1 (fr) * 1990-12-19 1992-06-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Chambre de combustion à contre-courant de longueur courte, et à formation réduite de NOx

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2155835B1 (fr) * 1971-10-08 1974-05-31 Snecma
US3751910A (en) * 1972-02-25 1973-08-14 Gen Motors Corp Combustion liner
US4297842A (en) * 1980-01-21 1981-11-03 General Electric Company NOx suppressant stationary gas turbine combustor
JPH0752014B2 (ja) * 1986-03-20 1995-06-05 株式会社日立製作所 ガスタ−ビン燃焼器
GB2221979B (en) * 1988-08-17 1992-03-25 Rolls Royce Plc A combustion chamber for a gas turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2482E (fr) * 1902-04-30 1904-04-27 Gaston Charles Emile De Bonnec Système de turbo-moteur à combustion continue
US4288980A (en) * 1979-06-20 1981-09-15 Brown Boveri Turbomachinery, Inc. Combustor for use with gas turbines
JPS60185025A (ja) * 1984-03-02 1985-09-20 Hitachi Ltd 再生サイクルガスタ−ビン用燃焼器ライナ
EP0491625A1 (fr) * 1990-12-19 1992-06-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Chambre de combustion à contre-courant de longueur courte, et à formation réduite de NOx

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 10, no. 29 (M - 451)<2086> 5 February 1986 (1986-02-05) *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH699309A1 (de) * 2008-08-14 2010-02-15 Alstom Technology Ltd Thermische maschine mit luftgekühlter, ringförmiger brennkammer.
EP2154431A2 (fr) * 2008-08-14 2010-02-17 Alstom Technology Ltd Machine thermique
EP2154431A3 (fr) * 2008-08-14 2010-08-04 Alstom Technology Ltd Machine thermique

Also Published As

Publication number Publication date
JPH06221555A (ja) 1994-08-09
DE4232442A1 (de) 1994-03-31

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

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