EP0845639B1 - Chambre de combustion et méthode d'exploitation - Google Patents

Chambre de combustion et méthode d'exploitation Download PDF

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Publication number
EP0845639B1
EP0845639B1 EP97810817A EP97810817A EP0845639B1 EP 0845639 B1 EP0845639 B1 EP 0845639B1 EP 97810817 A EP97810817 A EP 97810817A EP 97810817 A EP97810817 A EP 97810817A EP 0845639 B1 EP0845639 B1 EP 0845639B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
cross
stage
sectional constriction
sectional
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 - Lifetime
Application number
EP97810817A
Other languages
German (de)
English (en)
Other versions
EP0845639A1 (fr
Inventor
Oliver Christian Dr. Paschereit
Wolfgang Dr. Polifke
Thomas Dr. Sattelmayer
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 Technology GmbH
Original Assignee
Alstom Schweiz AG
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Filing date
Publication date
Application filed by Alstom Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP0845639A1 publication Critical patent/EP0845639A1/fr
Application granted granted Critical
Publication of EP0845639B1 publication Critical patent/EP0845639B1/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the present invention relates to a combustion chamber according to Preamble of Claim 1. It continues to apply Method for operating such a combustion chamber.
  • Helmholtz resonators in themselves are a significant reduction of pressure pulsations with vibrations close to the design frequency cause must not be misunderstood that in addition to the disadvantage of the necessary space for such a facility also has an impact on the environment of the Design frequency is limited.
  • GB 818 634 A is a combustion chamber with a first and a second level and an intermediate level Cross-sectional narrowing; this alone can do that on which the invention is based Problem not to be solved.
  • the invention seeks to remedy this.
  • the invention how it is characterized in the claims, the task lies based on a combustion chamber of the type mentioned to propose a design and an operating method that reflect the reflection of Pressure pulsations at the end of the combustion chamber minimized.
  • the main advantage of the invention is that due to the low-reflection design of the combustion chamber end the feedback of the pressure pulsations on the burner, which to renewed fluctuations in the heat release and thus Pressure pulsation can lead is prevented.
  • the basic idea of the invention is based on the idea that low-frequency vibrations are significantly absorbed, if it passes through a nozzle followed by a free jet be transmitted.
  • the invention a combustion chamber with two in the flow direction downstream stages.
  • burners At the top of the first stage are burners arranged, which in themselves can be of any design.
  • combustion chambers of the newer generation preferably to minimize pollutant emissions premix combustion are here for further consideration based on premix burner.
  • fuel and combustion air react within the first stage together.
  • the size of this first stage must be like this based on.
  • Fuel and combustion air react within the first stage with each other.
  • the size of this first Step must be dimensioned so that before reaching it Output in the direction of flow the heat from the combustion process is largely released.
  • the CO burnout must on the other hand not be completed.
  • This for its part must be dimensioned so that the CO content on the desired value drops before the working gases then the lead and Apply blades to a downstream turbine.
  • the transition is one of two stages existing combustion chamber, between the first and second Step formed with a narrowing of the cross section at which the low frequency vibrations are absorbed by this due to the narrowing called the contraction of the nozzle is trained, then transmitted with a free jet become.
  • the acoustic energy is transformed into the energy of the fluctuating vortex strength transferred at the nozzle outlet. This Eventually, energy is dissipated into heat.
  • the combustion chamber is switched by more than two sequentially Steps formed, so are the respective transitions of the individual stages in terms of cross-sectional narrowing or Nozzle contraction according to the two levels specified here To interpret principles.
  • the only figure shows one designed as an annular combustion chamber Combustion chamber, which consists of two stages, being intermediate a nozzle contraction acts between the two.
  • the figure shows how this results from the shaft axis 60 and rotary motion 61 of the rotor, not shown, shows that it is an annular combustion chamber in the present case essentially the shape of a coherent annular or has quasi-annular cylinder.
  • a such combustion chamber also from a number axially, quasi-axially or consist of helically arranged and individually self-contained combustion chambers.
  • On the combustion chamber can also consist of a single tube.
  • Annular combustion chamber consists of a first stage 20 and a second downstream stage 40. Intermediary between a cross-sectional constriction 30 acts on the two stages 20, 40, which will be discussed in more detail below.
  • the first Stage 20 initially has a number in the circumferential direction on the head side side-by-side premix burner 10 on, their design and function from EP-0 321 809 B1 evident. Another premix burner, which is also predestined to be used here arrive, emerges from EP-0 704 657 A2.
  • the mixture formation taking place in burner 10 forms between an air stream 12 and a fuel 10 that combustion mixture that in the first stage 20 to Hot gases 21 is burned. After flowing through the already cross-sectional constriction 30 flow the hot gases 21st then to the second stage 40, in which the final burnout takes place before the working gases 41 formed there finally act on a downstream turbine 50.
  • the design of the cross-sectional constriction 30 is permitted by the Pressure loss coefficient and the requirements for that Flow field defined. A nozzle shape is also possible minimized pressure loss coefficient or an orifice with a or more holes.
  • Crucial for the design of the Cross-sectional constriction 30 is, however, the area ratio contraction in the direction of flow. A minimal reflection is reached when the Mach number at outlet 31 of the cross-sectional constriction 30 equal to the area ratio of the cross-sectional constriction 30, which area ratio is made up of the quotient between exit area A2 divided by the Entry area A1 of cross-sectional constriction 30 is determined becomes.

Landscapes

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

Claims (5)

  1. Chambre de combustion, présentant un premier étage (20) et au moins un deuxième étage (40) monté derrière, caractérisée en ce que la chambre de combustion, lors du passage du premier au deuxième étage monté derrière, présente un rétrécissement de section transversale régulier et un élargissement de section transversale (31) irrégulier s'y raccordant.
  2. Chambre de combustion selon la revendication 1, caractérisée en ce que la longueur axiale (L) du rétrécissement de section transversale (30) est supérieure à 5% du diamètre au niveau de la surface d'entrée (A1).
  3. Chambre de combustion selon la revendication 1, - caractérisée en ce que la chambre de combustion est une chambre de combustion annulaire.
  4. Chambre de combustion selon la revendication 1, caractérisée en ce que le rétrécissement de section transversale (30) est une buse convergente.
  5. Procédé pour faire fonctionner une chambre de combustion de turbine à gaz, dans lequel on achemine au premier étage (20) de la chambre de combustion selon la revendication 1 un courant d'air (12) et un combustible (11), un mélange comburant est formé à partir du courant d'air et du combustible et est brûlé à l'intérieur du premier étage pour donner des gaz chauds (21), lesquels gaz chauds s'écoulent à travers le rétrécissement de section transversale (30) dans le deuxième étage (40) de la chambre de combustion, caractérisé en ce que pour l'obtention d'une réflexion minimale, le nombre de Mach de l'écoulement des gaz chauds est égal à la sortie (31) du rétrécissement de section transversale au rapport de surfaces du rétrécissement de section transversale, lequel rapport des surfaces est défini comme le quotient de la surface de sortie (A2) et de la surface d'entrée (A1) du rétrécissement de section transversale.
EP97810817A 1996-11-29 1997-10-31 Chambre de combustion et méthode d'exploitation Expired - Lifetime EP0845639B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19649486A DE19649486A1 (de) 1996-11-29 1996-11-29 Brennkammer
DE19649486 1996-11-29

Publications (2)

Publication Number Publication Date
EP0845639A1 EP0845639A1 (fr) 1998-06-03
EP0845639B1 true EP0845639B1 (fr) 2003-10-01

Family

ID=7813116

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810817A Expired - Lifetime EP0845639B1 (fr) 1996-11-29 1997-10-31 Chambre de combustion et méthode d'exploitation

Country Status (4)

Country Link
US (1) US6050078A (fr)
EP (1) EP0845639B1 (fr)
JP (1) JPH10169986A (fr)
DE (2) DE19649486A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3306320B2 (ja) * 1996-10-24 2002-07-24 株式会社東海 液体燃料用燃焼器具における燃焼芯
JP3285502B2 (ja) * 1996-10-30 2002-05-27 株式会社東海 液体燃料用燃焼器具
EP0985877A1 (fr) * 1998-09-10 2000-03-15 Abb Research Ltd. Dispositif et procédé pour réduire au minimum les vibrations thermoacoustques dans les chambres de combustion de turbines à gaz
EP1010939B1 (fr) * 1998-12-15 2004-02-11 ALSTOM (Switzerland) Ltd Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement
EP2236926B1 (fr) * 2009-03-17 2015-07-29 Siemens Aktiengesellschaft Dispositif de mesure de la température, turbine à gaz dotée d'un dispositif de mesure de la température et procédé de détermination directe de la température dans une chambre de combustion
US8484980B1 (en) 2009-11-19 2013-07-16 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Dual-mode combustor

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB818634A (en) * 1955-09-29 1959-08-19 Birmingham Small Arms Co Ltd Improvements in or relating to combustion chambers for gas turbines
BE551418A (fr) * 1955-10-28
US3905192A (en) * 1974-08-29 1975-09-16 United Aircraft Corp Combustor having staged premixing tubes
US3925002A (en) * 1974-11-11 1975-12-09 Gen Motors Corp Air preheating combustion apparatus
US4265615A (en) * 1978-12-11 1981-05-05 United Technologies Corporation Fuel injection system for low emission burners
US4420929A (en) * 1979-01-12 1983-12-20 General Electric Company Dual stage-dual mode low emission gas turbine combustion system
GB2098720B (en) * 1979-01-12 1983-04-27 Gen Electric Stationary gas turbine combustor arrangements
US4413477A (en) * 1980-12-29 1983-11-08 General Electric Company Liner assembly for gas turbine combustor
US4819438A (en) * 1982-12-23 1989-04-11 United States Of America Steam cooled rich-burn combustor liner
US4760695A (en) * 1986-08-28 1988-08-02 United Technologies Corporation Acoustic oscillatory pressure control for ramjet
JP2644745B2 (ja) * 1987-03-06 1997-08-25 株式会社日立製作所 ガスタービン用燃焼器
DE3707773C2 (de) * 1987-03-11 1996-09-05 Bbc Brown Boveri & Cie Einrichtung zur Prozesswärmeerzeugung
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
CH679799A5 (fr) * 1988-07-25 1992-04-15 Christian Reiter
US5158445A (en) * 1989-05-22 1992-10-27 Institute Of Gas Technology Ultra-low pollutant emission combustion method and apparatus
US5309718A (en) * 1992-09-14 1994-05-10 Hughes Aircraft Company Liquid fuel turbocharged power plant and method
CH687269A5 (de) * 1993-04-08 1996-10-31 Abb Management Ag Gasturbogruppe.
GB2278431A (en) * 1993-05-24 1994-11-30 Rolls Royce Plc A gas turbine engine combustion chamber
DE4426351B4 (de) * 1994-07-25 2006-04-06 Alstom Brennkammer für eine Gasturbine
DE4435266A1 (de) 1994-10-01 1996-04-04 Abb Management Ag Brenner
DE4446541A1 (de) * 1994-12-24 1996-06-27 Abb Management Ag Brennkammer
DE19520291A1 (de) * 1995-06-02 1996-12-05 Abb Management Ag Brennkammer

Also Published As

Publication number Publication date
EP0845639A1 (fr) 1998-06-03
JPH10169986A (ja) 1998-06-26
DE59710802D1 (de) 2003-11-06
DE19649486A1 (de) 1998-06-04
US6050078A (en) 2000-04-18

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