EP0122526B1 - Injecteur de combustible pour la chambre de combustion d'une turbine à gaz - Google Patents

Injecteur de combustible pour la chambre de combustion d'une turbine à gaz Download PDF

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Publication number
EP0122526B1
EP0122526B1 EP84103522A EP84103522A EP0122526B1 EP 0122526 B1 EP0122526 B1 EP 0122526B1 EP 84103522 A EP84103522 A EP 84103522A EP 84103522 A EP84103522 A EP 84103522A EP 0122526 B1 EP0122526 B1 EP 0122526B1
Authority
EP
European Patent Office
Prior art keywords
fuel
combustion chamber
nozzle outlet
lance
burner
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
Application number
EP84103522A
Other languages
German (de)
English (en)
Other versions
EP0122526A1 (fr
Inventor
Laan Dr. Hellat
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0122526A1 publication Critical patent/EP0122526A1/fr
Application granted granted Critical
Publication of EP0122526B1 publication Critical patent/EP0122526B1/fr
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement

Definitions

  • the invention relates to a burner with a fuel lance according to the preamble of claim 1.
  • the burner consists of a fixed gas line which is integrated in a mixing tube which can be moved by rotation.
  • This manual rotation of the mixing tube simultaneously and inevitably regulates the gas outlet cross section in the gas line and the air inlet cross section in the mixing tube.
  • the outlet cross-section for the mixture formed from gas and air is also regulated.
  • the regulation of the gas outlet cross-section takes place in that a displaceable sleeve encasing the gas line releases the desired gas passage cross-section.
  • the gas passage cross section consists of a number of gas passage holes distributed axially and over the circumference of the gas line.
  • the aim is not to restrict the fuel supply in the vicinity of the combustion chamber inlet, nor can one speak of sonic nozzles for the fuel supply, which only enable the fuel supply system to be decoupled acoustically.
  • the fuel quantity cannot be regulated over a wide range, which means that the burner described in DE-C-330 857 could only be used in a combustion chamber with a narrow power range.
  • the object of the invention is to provide a burner with a fuel lance, which enables the above-described decoupling of the burner fuel line to avoid combustion chamber vibrations, with the further possibility of being able to guarantee the fuel quantity regulation over a wide range.
  • the advantage of the invention can be seen essentially in the fact that a burner is created in a relatively simple manner, which combines both a decoupling of the fuel line to avoid combustion chamber vibrations and the possibility of regulating the fuel quantity over a wide range in a compact manner.
  • the decoupling is effective insofar as this compact design enables the distance between the throttle body and the nozzle outlet to be kept significantly shorter than the wavelength of typical settling of the combustion chamber system.
  • the fuel lance can optionally be designed with a central or radial nozzle outlet.
  • the throttle body also acts as a flame arrester.
  • Fig. 1 shows in a highly simplified manner the design of a fuel lance 1, which is part of a burner, not shown, which in turn is part of a combustion chamber, also not shown, e.g. a gas turbine.
  • the burner can be, for example, a diffusion burner with a swirled air supply.
  • the fuel lance 1 consists of a lance tube 2 with a central nozzle outlet 3. Upstream of the lance tube 2, the fuel lance 1 is formed by a bush 4 in which an axially adjustable tubular throttle body 5 is guided.
  • the fuel 7 is supplied through the tube interior 6. Downstream, the tube wall 8 in the unguided part of the throttle body 5 is provided with fuel passage openings 9 in the circumferential direction and in the axial direction.
  • the lance tube 2 carries a stamp 10 inside the tube, which is centered on the tube interior 6 of the throttle body 5 by means of webs 11 - as they are usually used for supporting internal bodies with cross-sections flowing through them.
  • a seal 12 also placed there ensures that the fuel passage openings 9 located above the plunger 10 in the respective axial position of the throttle body 5 are closed gas-tight. The gas tightness between the throttle body 5 and the bush 4 is brought about by a seal 13.
  • the free cross section - i.e. the number of fuel passage openings 9 still in use - and thus the fuel quantity 7a flowing through - are changed.
  • the released flow cross section thus depends on the respective penetration depth of the plunger 10 relative to the throttle body 5. If the ratio of the fuel pressure in the supply line to the pressure at the nozzle outlet 3 exceeds a critical value, the fuel 7 flows through the fuel passage openings 9 in the throttle body 5 at the speed of sound, so that pressure disturbances running upstream from the nozzle outlet 3 no longer influence the fuel quantity 7a emerging from the fuel passage openings 9 can.
  • the distance between fuel passage openings 9 and nozzle outlet 3 or 15 is considerably shorter than the wavelength of typical natural vibrations of the combustion chamber system.
  • FIG. 2 similar to FIG. 1, a greatly simplified illustration of a fuel lance 1 is also shown.
  • This embodiment is distinguished from FIG. 1 by the difference that the fuel quantity 7a flowing through now emerges radially from the fuel lance 1.
  • the lance tube 2 is continuously cylindrical and is open on the nozzle outlet side.
  • the punch 10 is extended over the webs 11 and carries a central body 14 at its end. The opening between the end of the lance tube 2 and the inside runout curve of the central body 14 forms the radial nozzle outlet 15.
  • the fuel 7 is fed directly through the fuel lance 1. Downstream the lance tube 2 runs into a bushing 16 which extends up to the central nozzle outlet 3.
  • the throttle body 5 is a spindle which is only tubularly recessed at the end and only over a certain length.
  • the fuel passage openings 9 are also provided in this section.
  • the inner diameter of the sleeve 16 also forms the opening to the central nozzle outlet 3.
  • the fuel flows through those fuel passage openings 9 which are still in use due to the fuel quantity regulation, i.e. are not yet encased by the sleeve 16.
  • the fuel 7 flows from the outside into the interior of the throttle body 5 in order to reach the nozzle outlet 3 from here.
  • Fig. 4 shows a lance tube 2 open on both sides, which is divided in the middle by a constriction 17.
  • the constriction fulfills the same function as the bushing 16, described under FIG. 3.
  • the central body 14 enables a radial nozzle outlet 15.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Spray-Type Burners (AREA)

Claims (3)

1. - Brûleur à injecteur de combustible pour l'admission d'un combistible gazeux ou d'un mélange de combustible et d'air dans la chambre de combustion d'une turbine à gaz, caractérisé en ce que l'injecteur de combustible (1) porte un élément étrangleur intérieur (5) mobile axialement par rapport à un élément fixe (10, 16, 17), cet élément mobile étant pourvu, du côté de sortie du combustible, d'un certain nombre d'orifices de passage de combustible (9) orientés vers la sortie (3, 15) de l'injecteur et la quantité de combustible (7a) qui passe par les orifices de passage de combustible (9) à la vitesse du son dans des conditions de pression plus que supercritiques, dépendant de la profondeur d'enfoncement de l'élément étrangleur (5) par rapport à l'élément fixe (10,16,17) dans la zone des orifices de passage de combustible (9) dont l'éloignement de la sortie (3, 15) de l'injectrur est nettement inférieur à la longueur d'onde des oscillations propres typiques du système de chambre de combustion.
2.- Brûleur suivant la revendication 1, caractérisé en ce que la sortie (3) de l'injecteur est une sortie centrale.
3.- Brûleur suivant la revendication 1, caractérisé en ce que la sortir (15) de l'injecteur s'ouvre radialement dans la chambre de combustion.
EP84103522A 1983-04-13 1984-03-30 Injecteur de combustible pour la chambre de combustion d'une turbine à gaz Expired EP0122526B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH1988/83 1983-04-13
CH198883 1983-04-13

Publications (2)

Publication Number Publication Date
EP0122526A1 EP0122526A1 (fr) 1984-10-24
EP0122526B1 true EP0122526B1 (fr) 1987-05-20

Family

ID=4223287

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84103522A Expired EP0122526B1 (fr) 1983-04-13 1984-03-30 Injecteur de combustible pour la chambre de combustion d'une turbine à gaz

Country Status (4)

Country Link
US (1) US4761958A (fr)
EP (1) EP0122526B1 (fr)
JP (1) JPS59197736A (fr)
DE (1) DE3463836D1 (fr)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3913334A1 (de) * 1989-04-22 1990-10-25 Caldyn Apparatebau Gmbh Vorrichtung fuer die zerstaeubung von fluessigkeit oder fuer die zerteilung von gas in kleine blasen
US5266025A (en) * 1992-05-27 1993-11-30 Praxair Technology, Inc. Composite lance
US5218824A (en) * 1992-06-25 1993-06-15 Solar Turbines Incorporated Low emission combustion nozzle for use with a gas turbine engine
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
US6269646B1 (en) 1998-01-28 2001-08-07 General Electric Company Combustors with improved dynamics
CA2330609C (fr) * 1998-05-04 2005-02-15 Cuyuna Engine Company Inc. Doing Business As 2 Stroke International Moteur polycarburant
GB9811577D0 (en) * 1998-05-30 1998-07-29 Rolls Royce Plc A fuel injector
JP2002531805A (ja) 1998-12-08 2002-09-24 シーメンス アクチエンゲゼルシヤフト 燃焼装置および燃焼方法
WO2000034715A1 (fr) * 1998-12-09 2000-06-15 Abb Alstom Power Uk Ltd. Modification de la dynamique de reaction de combustion
GB9827051D0 (en) * 1998-12-09 1999-02-03 Alstom Gas Turbines Ltd Gas reaction chamber
EP1096201A1 (fr) * 1999-10-29 2001-05-02 Siemens Aktiengesellschaft Brûleur
FR2822940A1 (fr) * 2001-08-10 2002-10-04 Air Liquide Procede, lance et tuyere d'injection d'oxygene radialement dans un four
DE10164099A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeinspritzung
US6820431B2 (en) * 2002-10-31 2004-11-23 General Electric Company Acoustic impedance-matched fuel nozzle device and tunable fuel injection resonator assembly
KR101701275B1 (ko) 2012-02-16 2017-02-01 하이만 센서 게엠베하 높은 충전 레벨을 갖는 써모파일 적외선 센서 구조물
KR20190132563A (ko) 2012-02-27 2019-11-27 디이이씨 아이엔씨 내연 기관을 추진하기 위한 산소-풍부 플라즈마 발생기
BR112018068006A2 (pt) 2016-03-07 2019-01-15 Hytech Power Inc método para gerar e distribuir um segundo combustível para um motor de combustão interna
CN107062307B (zh) * 2017-05-09 2023-06-20 新奥能源动力科技（上海）有限公司 一种燃气轮机燃烧室
US20190234348A1 (en) 2018-01-29 2019-08-01 Hytech Power, Llc Ultra Low HHO Injection
JP6950876B2 (ja) * 2018-09-06 2021-10-13 株式会社Ihi 液体燃料噴射体
CN117469696B (zh) * 2022-11-25 2024-05-28 中国航空发动机研究院 一种燃油喷杆及燃油喷射装置

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE330857C (de) * 1918-09-06 1920-12-22 Selas Akt Ges Gasbrenner fuer Niederdruckgasfeuerungen mit gleichzeitiger Regelung der Gas- und Luftzufuhr
US2775484A (en) * 1953-08-31 1956-12-25 Phillips Petroleum Co Viscosity compensating variable-area fuel nozzle
GB805463A (en) * 1954-09-08 1958-12-03 Fuel Firing Ltd Improvements in the control of fluid flow
GB1051666A (fr) * 1962-01-10 1900-01-01
DE1919488B2 (de) * 1969-04-17 1971-11-18 Mtu Muenchen Gmbh Brennstoffeinspritzeinrichtung fuer gasturbinen
US3695037A (en) * 1970-09-08 1972-10-03 Teledyne Ind Shaft mounted fuel control
US3726088A (en) * 1971-08-20 1973-04-10 Us Navy On-demand variable flow closed loop gas generator system with a variable area injector
DE2227281A1 (de) * 1972-06-05 1973-12-20 Helmut Just Allgas-trichtermischduese fuer geblaesebrenner
JPS5545939Y2 (fr) * 1975-02-14 1980-10-28
FR2315051A1 (fr) * 1975-06-20 1977-01-14 Bertin & Cie Vanne insonorisee
CA1123332A (fr) * 1977-11-10 1982-05-11 John Maksim, Jr. Bruleurs pour fours d'egalisation, installations d'egalisation equipees desdits bruleurs, et methode de chauffage desdits fours
US4257762A (en) * 1978-09-05 1981-03-24 John Zink Company Multi-fuel gas burner using preheated forced draft air
JPS5920062B2 (ja) * 1980-01-25 1984-05-10 株式会社クボタ スリ−ブ弁

Also Published As

Publication number Publication date
JPS59197736A (ja) 1984-11-09
EP0122526A1 (fr) 1984-10-24
JPH0531050B2 (fr) 1993-05-11
US4761958A (en) 1988-08-09
DE3463836D1 (en) 1987-06-25

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