EP0602404A1 - Chambre de combustion pour turbine à gaz - Google Patents

Chambre de combustion pour turbine à gaz Download PDF

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Publication number
EP0602404A1
EP0602404A1 EP93118569A EP93118569A EP0602404A1 EP 0602404 A1 EP0602404 A1 EP 0602404A1 EP 93118569 A EP93118569 A EP 93118569A EP 93118569 A EP93118569 A EP 93118569A EP 0602404 A1 EP0602404 A1 EP 0602404A1
Authority
EP
European Patent Office
Prior art keywords
combustion
combustion chamber
zone
region
constant
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
EP93118569A
Other languages
German (de)
English (en)
Other versions
EP0602404B1 (fr
Inventor
Burkhard Dr. Schulte-Werning
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 EP0602404A1 publication Critical patent/EP0602404A1/fr
Application granted granted Critical
Publication of EP0602404B1 publication Critical patent/EP0602404B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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

Definitions

  • the invention relates to a gas turbine combustion chamber according to the preamble of the claim.
  • combustion Different types of heat supply (combustion) are possible in a combustion chamber in terms of gas dynamics.
  • combustion with a constant cross-section is of primary practical importance.
  • the invention tries to avoid all these disadvantages. It is based on the task of creating a gas turbine combustion chamber in which the total pressure loss and the combustion chamber length are small at the same time.
  • this is achieved in a gas turbine combustion chamber, which consists of an inflow zone with injection, ignition delay zone, reaction zone, burnout zone and transition zone to the turbine, in that the reaction zone has a widening cross section such that the combustion is gas dynamic at constant pressure or at a constant Mach number is feasible.
  • the advantages of the invention are that, as a result of the combustion at a constant Mach number or at a constant pressure, only a small total pressure loss is caused and the combustion chamber length is reduced. As a result, the efficiency and performance of the combustion chamber are significantly better than in the prior art.
  • a combustion chamber according to the invention is shown schematically in FIG. 1.
  • the ratio of the combustion chamber height at the beginning of reaction zone 3 to the length of reaction zone 3 is approximately one.
  • half the duct opening angle ⁇ can easily be taken into account in the combustion chamber design.
  • the constant pressure combustion at which the flow velocity u is constant, is the most favorable.
  • FIG. 1 A combustion chamber optimized in this sense is shown in FIG. 1.
  • the ignition delay zone 2 is designed as a conventional diffuser.
  • the reaction zone 3 the cross-sectional expansion according to the invention to such a mass has taken place that the combustion takes place at constant pressure.
  • the burnout zone 4 which has a constant (largest) cross section.
  • the transition zone 4 to the turbine is designed with a conventional nozzle geometry.
  • FIG. 2 Another embodiment of the invention is shown schematically in FIG. 2 on the longitudinal section of a combustion chamber.
  • the combustion chamber is designed in such a way that a constant Mach number is ensured in the reaction zone 3 by a suitable cross-sectional expansion being superimposed on the heat supply by the chemical reaction in this combustion process.
  • Half the channel opening angle ⁇ is smaller here than in the first embodiment.
  • the inflow zone 1, the ignition delay zone 2 and the burnout zone 4 can of course be structurally similar to those in embodiment 1 or also have other geometric shapes, as shown in a variant in FIG. 2.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)
EP93118569A 1992-12-17 1993-11-18 Chambre de combustion pour turbine à gaz Expired - Lifetime EP0602404B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4242650 1992-12-17
DE4242650A DE4242650A1 (de) 1992-12-17 1992-12-17 Gasturbinenbrennkammer

Publications (2)

Publication Number Publication Date
EP0602404A1 true EP0602404A1 (fr) 1994-06-22
EP0602404B1 EP0602404B1 (fr) 1997-09-03

Family

ID=6475557

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93118569A Expired - Lifetime EP0602404B1 (fr) 1992-12-17 1993-11-18 Chambre de combustion pour turbine à gaz

Country Status (4)

Country Link
US (1) US5465577A (fr)
EP (1) EP0602404B1 (fr)
JP (1) JPH06221557A (fr)
DE (2) DE4242650A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6213489B1 (en) 1998-07-08 2001-04-10 Meritor Heavy Vehicle Technology, Llc Operating system for locking pins for sliding undercarriages
DE10250101A1 (de) * 2002-10-28 2004-05-06 Alstom (Switzerland) Ltd. Verbesserter Brenner für einen Wärmeerzeuger
US10876732B2 (en) * 2016-10-19 2020-12-29 Gloyer-Taylor Laboratories Llc Scalable acoustically-stable combustion chamber and design methods
CN110732888B (zh) 2018-07-20 2022-07-26 米沃奇电动工具公司 工具刀头夹持器

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2541170A (en) * 1946-07-08 1951-02-13 Kellogg M W Co Air intake arrangement for air jacketed combustion chambers
US2565308A (en) * 1945-01-17 1951-08-21 Research Corp Combustion chamber with conical air diffuser
DE847091C (de) * 1944-05-13 1952-08-21 Daimler Benz Ag Heissluftstrahltriebwerk
GB1541408A (en) * 1968-08-12 1979-02-28 Snecma Combustion chambers operating on a supersonic stream chiefly for jet engines

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2685421A (en) * 1950-08-30 1954-08-03 G M Giannini & Co Inc Aircraft nose mounting for jet engines
GB736823A (en) * 1953-01-19 1955-09-14 Lucas Industries Ltd Engine combustion chambers
DE1046954B (de) * 1953-03-26 1958-12-18 Herbert Troeger Verbrennungsturbine mit zugleich als Expansionsduesen wirkenden Brennkammern
US3783616A (en) * 1961-03-02 1974-01-08 Garrett Corp Control method for detonation combustion engines
US3372542A (en) * 1966-11-25 1968-03-12 United Aircraft Corp Annular burner for a gas turbine
GB1253097A (fr) * 1969-03-21 1971-11-10
US4146357A (en) * 1975-07-30 1979-03-27 Hotwork International Limited Fuel fired burners
GB1556414A (en) * 1975-08-11 1979-11-21 Flight Dynamics Res Ejector assembly for thrust augmentation and a method of operating the assembly
DE2629761A1 (de) * 1976-07-02 1978-01-05 Volkswagenwerk Ag Brennkammer fuer gasturbinen
JPS5857655B2 (ja) * 1976-08-27 1983-12-21 株式会社日立製作所 ガスタ−ビン用燃焼器
US4947641A (en) * 1988-06-23 1990-08-14 Sundstrand Corporation Pulse accelerating turbine
DE9207469U1 (de) * 1992-06-03 1992-08-13 Nerenberg, Gerhard, 2400 Lübeck Gasturbine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE847091C (de) * 1944-05-13 1952-08-21 Daimler Benz Ag Heissluftstrahltriebwerk
US2565308A (en) * 1945-01-17 1951-08-21 Research Corp Combustion chamber with conical air diffuser
US2541170A (en) * 1946-07-08 1951-02-13 Kellogg M W Co Air intake arrangement for air jacketed combustion chambers
GB1541408A (en) * 1968-08-12 1979-02-28 Snecma Combustion chambers operating on a supersonic stream chiefly for jet engines

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
BOYCE: "GAS TURBINE ENGINERING HANDBOOK", 1983, GULF, HOUSTON (USA) *
KOSMOWSKI: "TURBOMASCHINEN", HEIDELBERG, HUTHIG., HEIDELBERG (DE) *
SAWYER: "GAS TURBINE CONSTRUCTION", 1947, PRENTICE HALL, NEW YORK *
SPALDING: "SOME FUNDAMENTALS OF COMBUSTION", 1955, BUTTERWORTHS, LONDON, 6696 *

Also Published As

Publication number Publication date
DE4242650A1 (de) 1994-06-23
DE59307265D1 (de) 1997-10-09
EP0602404B1 (fr) 1997-09-03
US5465577A (en) 1995-11-14
JPH06221557A (ja) 1994-08-09

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