EP0845639A1 - Chambre de combustion - Google Patents

Chambre de combustion Download PDF

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Publication number
EP0845639A1
EP0845639A1 EP97810817A EP97810817A EP0845639A1 EP 0845639 A1 EP0845639 A1 EP 0845639A1 EP 97810817 A EP97810817 A EP 97810817A EP 97810817 A EP97810817 A EP 97810817A EP 0845639 A1 EP0845639 A1 EP 0845639A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
cross
sectional constriction
stage
chamber according
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
EP97810817A
Other languages
German (de)
English (en)
Other versions
EP0845639B1 (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
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 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.
  • 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 the effect on the environment the design frequency is limited.
  • 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 propose a configuration that reflects the reflection of Pressure pulsations at the end of the combustion chamber minimized.
  • the main advantage of the invention is that that due to the low-reflection design of the combustion chamber end the feedback of the pressure pulsations on the burner, which lead to renewed fluctuations in heat release and so that pressure pulsations can cause 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.
  • Arranged burner which can be of any design can.
  • premix burners for further consideration premix burners 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 and impeller blades of a downstream turbine.
  • the transition is one of two stages existing combustion chamber, between the first and second Step formed with a cross-sectional constriction, 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 will.
  • 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 are 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 helically arranged and individually self-contained Combustion chambers exist.
  • the combustion chamber also consist of a single tube.
  • the one shown in the figure Annular combustion chamber consists of a first stage 20 and a second downstream stage 40. intermediate 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 on the head side in the circumferential direction side-by-side premix burner 10 whose design and function from EP-0 321 809 B1 emerges, this document integrating component present description is.
  • Another premix burner which is also predestined to be used here arrive, emerges from EP-0 704 657 A2, whereby this too Document integral part of this description is.
  • the mixture formation taking place in the 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 mentioned 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, this area ratio being made up of the quotient between exit area A2 divided by the Entry area A1 of the cross-sectional constriction 30 is determined becomes. This specification ensures that there is sufficient progress the nozzle contraction reaches a minimal reflection, i.e.

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)
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 true EP0845639A1 (fr) 1998-06-03
EP0845639B1 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)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6010334A (en) * 1996-10-30 2000-01-04 Tokai Corporation Combustion appliance for liquid fuel
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
US6113385A (en) * 1996-10-24 2000-09-05 Tokai Corporation Combustion wick for liquid fuel combustion appliances

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB812201A (en) * 1955-10-28 1959-04-22 Snecma Improvements in combustion equipment for continuous-flow internal combustion engines
GB818634A (en) * 1955-09-29 1959-08-19 Birmingham Small Arms Co Ltd Improvements in or relating to combustion chambers for gas turbines
US4413477A (en) * 1980-12-29 1983-11-08 General Electric Company Liner assembly for gas turbine combustor
EP0353192A1 (fr) * 1988-07-25 1990-01-31 Christian Reiter Génération contrôlable de jet de gaz propulsif
US5309718A (en) * 1992-09-14 1994-05-10 Hughes Aircraft Company Liquid fuel turbocharged power plant and method
EP0704657A2 (fr) 1994-10-01 1996-04-03 ABB Management AG Brûleur

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
GB2098720B (en) * 1979-01-12 1983-04-27 Gen Electric Stationary gas turbine combustor arrangements
US4420929A (en) * 1979-01-12 1983-12-20 General Electric Company Dual stage-dual mode low emission gas turbine combustion system
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
US5158445A (en) * 1989-05-22 1992-10-27 Institute Of Gas Technology Ultra-low pollutant emission combustion method and apparatus
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
DE4446541A1 (de) * 1994-12-24 1996-06-27 Abb Management Ag Brennkammer
DE19520291A1 (de) * 1995-06-02 1996-12-05 Abb Management Ag Brennkammer

Patent Citations (6)

* 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
GB812201A (en) * 1955-10-28 1959-04-22 Snecma Improvements in combustion equipment for continuous-flow internal combustion engines
US4413477A (en) * 1980-12-29 1983-11-08 General Electric Company Liner assembly for gas turbine combustor
EP0353192A1 (fr) * 1988-07-25 1990-01-31 Christian Reiter Génération contrôlable de jet de gaz propulsif
US5309718A (en) * 1992-09-14 1994-05-10 Hughes Aircraft Company Liquid fuel turbocharged power plant and method
EP0704657A2 (fr) 1994-10-01 1996-04-03 ABB Management AG Brûleur

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6113385A (en) * 1996-10-24 2000-09-05 Tokai Corporation Combustion wick for liquid fuel combustion appliances
US6010334A (en) * 1996-10-30 2000-01-04 Tokai Corporation Combustion appliance for liquid fuel
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

Also Published As

Publication number Publication date
DE59710802D1 (de) 2003-11-06
JPH10169986A (ja) 1998-06-26
EP0845639B1 (fr) 2003-10-01
DE19649486A1 (de) 1998-06-04
US6050078A (en) 2000-04-18

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