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EP0781967A3 - Annular combustion chamber for gas turbine - Google Patents

Annular combustion chamber for gas turbine Download PDF

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Publication number
EP0781967A3
EP0781967A3 EP96810777A EP96810777A EP0781967A3 EP 0781967 A3 EP0781967 A3 EP 0781967A3 EP 96810777 A EP96810777 A EP 96810777A EP 96810777 A EP96810777 A EP 96810777A EP 0781967 A3 EP0781967 A3 EP 0781967A3
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
downstream
gas turbine
compressor
fuel injection
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
Application number
EP96810777A
Other languages
German (de)
French (fr)
Other versions
EP0781967A2 (en
EP0781967B1 (en
Inventor
Klaus Dr. Döbbeling
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.)
General Electric Switzerland GmbH
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Publication of EP0781967A2 publication Critical patent/EP0781967A2/en
Publication of EP0781967A3 publication Critical patent/EP0781967A3/en
Application granted granted Critical
Publication of EP0781967B1 publication Critical patent/EP0781967B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F23R3/02—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
    • 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
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

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)

Abstract

Bei einer Gasturbinenringbrennkammer (4), welche stromab eines Verdichters (1) angeordnet und auf ihrer Frontplatte mit mindestens einer ringförmig angeordneten Reihe von Vormischbrennern (5) bestückt ist, führt direkt stromab des Verdichteraustritts von den Leitschaufeln (9) der letzten Verdichterreihe zu jedem Brenner (5) jeweils ein als Diffusor ausgebildeter Brennluftkanal (15), an dessem stromabwärtigen Ende sich mindestens ein Längswirbelerzeuger (16) befindet, wobei im oder stromab des Längswirbelerzeugers (16) mindestens eine Brennstoffeindüsung (17) vorgesehen ist. Stromab der Brennstoffeindüsung (17) ist ein in die Brennkammer (4) endender Mischkanal (19) konstanter Höhe (H) und mit einer Länge (L), die etwa dem zweifachen Wert des hydraulischen Kanaldurchmessers (D) entspricht, angeordnet. Dadurch kann die Baugrösse der Gasturbine im Bereich der Brennkammer (4) wesentlich reduziert werden. Zusätzlich verringert sich der Druckverlust zwischen Verdichteraustritt und Turbineneintritt.

Figure 00000001
In a gas turbine ring combustion chamber (4), which is arranged downstream of a compressor (1) and is equipped on its front plate with at least one ring-shaped row of premix burners (5), leads directly downstream of the compressor outlet from the guide vanes (9) of the last compressor row to each burner (5) each have a combustion air duct (15) designed as a diffuser, at the downstream end of which there is at least one longitudinal vortex generator (16), at least one fuel injection (17) being provided in or downstream of the longitudinal vortex generator (16). Downstream of the fuel injection (17) there is a mixing channel (19) of constant height (H) and a length (L) which ends in the combustion chamber (4) and corresponds to approximately twice the value of the hydraulic channel diameter (D). As a result, the size of the gas turbine in the region of the combustion chamber (4) can be significantly reduced. In addition, the pressure loss between the compressor outlet and the turbine inlet is reduced.
Figure 00000001
EP96810777A 1995-12-29 1996-11-12 Annular combustion chamber for gas turbine Expired - Lifetime EP0781967B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19549143A DE19549143A1 (en) 1995-12-29 1995-12-29 Gas turbine ring combustor
DE19549143 1995-12-29

Publications (3)

Publication Number Publication Date
EP0781967A2 EP0781967A2 (en) 1997-07-02
EP0781967A3 true EP0781967A3 (en) 1999-04-07
EP0781967B1 EP0781967B1 (en) 2003-04-02

Family

ID=7781645

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810777A Expired - Lifetime EP0781967B1 (en) 1995-12-29 1996-11-12 Annular combustion chamber for gas turbine

Country Status (5)

Country Link
US (1) US5839283A (en)
EP (1) EP0781967B1 (en)
JP (1) JPH09196379A (en)
CN (1) CN1088151C (en)
DE (2) DE19549143A1 (en)

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Also Published As

Publication number Publication date
DE19549143A1 (en) 1997-07-03
JPH09196379A (en) 1997-07-29
EP0781967A2 (en) 1997-07-02
US5839283A (en) 1998-11-24
CN1088151C (en) 2002-07-24
DE59610298D1 (en) 2003-05-08
EP0781967B1 (en) 2003-04-02
CN1158383A (en) 1997-09-03

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