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EP0584661B1 - Procédé de production d'un courant de gaz combustible dans un générateur de chaleur et générateur pour sa mise en oeuvre - Google Patents

Procédé de production d'un courant de gaz combustible dans un générateur de chaleur et générateur pour sa mise en oeuvre Download PDF

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Publication number
EP0584661B1
EP0584661B1 EP19930112919 EP93112919A EP0584661B1 EP 0584661 B1 EP0584661 B1 EP 0584661B1 EP 19930112919 EP19930112919 EP 19930112919 EP 93112919 A EP93112919 A EP 93112919A EP 0584661 B1 EP0584661 B1 EP 0584661B1
Authority
EP
European Patent Office
Prior art keywords
fuel
heat generator
nozzle
wall
gas
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
EP19930112919
Other languages
German (de)
English (en)
Other versions
EP0584661A1 (fr
Inventor
Rolf Dr. Althaus
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 EP0584661A1 publication Critical patent/EP0584661A1/fr
Application granted granted Critical
Publication of EP0584661B1 publication Critical patent/EP0584661B1/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Definitions

  • the present invention relates to a method according to the preamble of claim 1. It also relates to a heat generator for carrying out the method.
  • EP-A-0 244 972 discloses a method for generating a combustible gas stream in a heat generator, which is accomplished by adding fuel to the gas stream flowing through the heat generator.
  • the gas stream is interspersed with a fuel directed at an angle to it, an additional mass being added to the fuel beforehand.
  • Such a configuration is not suitable for controlling the ignition timing, which means that the flame must re-ignite during operation.
  • the object that is achieved with the present invention is to provide a method and a heat generator for carrying out the method in which the distribution of the fuel and the control of the timing of the ignition of the combustible gas stream are improved.
  • a heat generator 12 is located between a high-pressure turbine 10 and a low-pressure turbine 11.
  • This heat generator 12 has a combustion chamber 13 designed as an annular space, which is characterized by an essentially cylindrical, or more precisely frustoconical outer wall 14 and a corresponding inner wall 15 is limited.
  • a number of fuel injectors 16 are fastened evenly distributed around the circumference. These fuel nozzles 16 are arranged essentially radially inwards (FIG. 2) and transversely to the exhaust gas flow (FIG. 1). These fuel nozzles 16 are arranged in two cross-sectional planes 17 and 18, which are at a distance L from one another. The design of these fuel injection nozzles 16 can be seen in FIG. 3.
  • each fuel injector 16 is surrounded by a gas nozzle 19 and an air nozzle 20.
  • the mouth 22 of this fuel injection nozzle 16 is located in the region of the wall of the combustion chamber 13. Since the combustion chamber 13 is designed as an annular space, the surface of the heat generator 12 to be cooled becomes relatively small, and the heat generator 12 is also designed symmetrically.
  • the fuel can be supplied as a transverse jet to the gas stream emerging from the high pressure turbine. The momentum of the fuel mass flow must be large enough to produce a relatively quick and efficient mixing.
  • the fuel-gas mixture ignites automatically after about one millisecond. Flame stabilization is not necessary with this type of combustion.
  • the ignition timing can be controlled by a screen air flow from the air nozzle 20, which is blown in coaxially with the fuel, thereby preventing re-ignition.
  • the fuel can be extended over a length L are added in stages, ie there are a number of fuel injection nozzles 16 distributed uniformly around the circumference in a first cross-sectional plane 17 and a further number of fuel injection nozzles 16 are also arranged uniformly distributed around the circumference in a second cross-sectional plane 18, which are preferably arranged offset in relation to one another in the circumferential direction .
  • a number of injection nozzles 21 are preferably arranged on the inner combustion chamber wall 15, which, in contrast to the radially inwardly directed injection nozzles 16 mentioned above, are directed radially outwards is.
  • the gases emerging from the high-pressure turbine 10 flow through the heat generator 12 and then reach the low-pressure turbine 11, as indicated by arrows A.
  • the gases flowing through the heat generator 12 were enriched with fuel with the aid of the fuel injection nozzles 16 and 21. Since the gas-enriched gas stream ignites immediately, its temperature is raised and reaches the low-pressure turbine 11 at the desired temperature and pressure.
  • the screen air flow from the nozzle 20 has an inhibitory effect because the air is cooler, so that the ignition point of the combustible gas flow can be delayed.

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

Claims (7)

  1. Procédé pour produire un flux de gaz combustible dans un générateur de chaleur par adjonction de combustible au flux de gaz traversant le générateur de chaleur, sachant que le flux de gaz est entremêlé au moins en partie à un flux de combustible qui lui est transversal, et sachant qu'une masse d'appoint est préalablement ajoutée au flux de combustible, caractérisé en ce que le point d'allumage est contrôlé par un flux d'air-écran qui sort d'au moins une buse d'air (19, 20) et qui est insufflé coaxialement au flux de combustible sortant d'une buse de combustible (16, 21).
  2. Générateur de chaleur pour l'exécution du procédé suivant la revendication 1, comprenant une chambre de combustion pour guider des gaz d'échappement provenant d'une turbomachine qui fonctionne en amont, au moins une buse de combustible, qui est dirigée transversalement à la paroi de la chambre de combustion, caractérisé en ce que la buse de combustible (16, 21) est entourée d'au moins une buse d'air (19, 20).
  3. Générateur de chaleur suivant la revendication 2, caractérisé en ce que la chambre de combustion (13) est conçue annulaire et comporte un certain nombre de buses de combustible (16, 21) uniformément réparties sur sa périphérie.
  4. Générateur de chaleur suivant la revendication 3, caractérisé en ce que la chambre de combustion annulaire (13) comporte une paroi extérieure (14) et une paroi intérieure (15), et que les buses de combustible (16) sont dirigées au niveau de la paroi extérieure (14) radialement vers l'intérieur.
  5. Générateur de chaleur suivant la revendication 4, caractérisé en ce qu'en plus des buses de combustible (16) dirigées radialement vers l'intérieur, d'autres buses de combustible (21) dirigées radialement vers l'extérieur sont disposées au niveau de la paroi intérieure.
  6. Générateur de chaleur suivant les revendications 4 et 5, caractérisé en ce que les buses de combustible (16, 21) sont disposées de manière progressive dans la direction axiale de la chambre de combustion (13), et que les buses de combustible (16, 21) sont décalées les unes par rapport aux autres dans les différents plans de l'agencement progressif.
  7. Générateur de chaleur suivant la revendication 2, caractérisé en ce qu'une base (19) acheminant du gaz est disposée en forme d'anneau autour des buses de combustible (16, 21) et qu'une buse (20) acheminant de l'air est disposée en forme d'anneau autour de la base acheminant du gaz.
EP19930112919 1992-08-28 1993-08-12 Procédé de production d'un courant de gaz combustible dans un générateur de chaleur et générateur pour sa mise en oeuvre Expired - Lifetime EP0584661B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2681/92 1992-08-28
CH268192 1992-08-28

Publications (2)

Publication Number Publication Date
EP0584661A1 EP0584661A1 (fr) 1994-03-02
EP0584661B1 true EP0584661B1 (fr) 1997-05-28

Family

ID=4239189

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19930112919 Expired - Lifetime EP0584661B1 (fr) 1992-08-28 1993-08-12 Procédé de production d'un courant de gaz combustible dans un générateur de chaleur et générateur pour sa mise en oeuvre

Country Status (3)

Country Link
EP (1) EP0584661B1 (fr)
JP (1) JP3452610B2 (fr)
DE (1) DE59306570D1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6289666B1 (en) * 1992-10-27 2001-09-18 Ginter Vast Corporation High efficiency low pollution hybrid Brayton cycle combustor
USRE43252E1 (en) 1992-10-27 2012-03-20 Vast Power Portfolio, Llc High efficiency low pollution hybrid Brayton cycle combustor

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1800611A1 (de) * 1968-10-02 1970-05-27 Hertel Dr Ing Heinrich Anordnung zum Einspritzen von Kraftstoff in einen an einer Einspritzduese mit UEberschallgeschwindigkeit vorbeistroemenden Luftstrom
FR2081220A1 (fr) * 1970-03-19 1971-12-03 Hertel Heinrich
EP0244972B1 (fr) * 1986-05-03 1990-09-19 LUCAS INDUSTRIES public limited company Chambre de combustion pour carburant liquide

Also Published As

Publication number Publication date
JPH06185730A (ja) 1994-07-08
EP0584661A1 (fr) 1994-03-02
JP3452610B2 (ja) 2003-09-29
DE59306570D1 (de) 1997-07-03

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