EP0882932B1 - Chambre de combustion - Google Patents

Chambre de combustion Download PDF

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Publication number
EP0882932B1
EP0882932B1 EP98810304A EP98810304A EP0882932B1 EP 0882932 B1 EP0882932 B1 EP 0882932B1 EP 98810304 A EP98810304 A EP 98810304A EP 98810304 A EP98810304 A EP 98810304A EP 0882932 B1 EP0882932 B1 EP 0882932B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
plenum
chamber according
bypass
downstream
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
EP98810304A
Other languages
German (de)
English (en)
Other versions
EP0882932A3 (fr
EP0882932A2 (fr
Inventor
Leif Andersson
Peter Dr. Jansohn
Jonathan Lloyd
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 Switzerland GmbH
Original Assignee
Alstom Schweiz AG
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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP0882932A2 publication Critical patent/EP0882932A2/fr
Publication of EP0882932A3 publication Critical patent/EP0882932A3/fr
Application granted granted Critical
Publication of EP0882932B1 publication Critical patent/EP0882932B1/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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/02—Disposition of air supply not passing through burner
    • F23C7/06—Disposition of air supply not passing through burner for heating the incoming air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines

Definitions

  • the invention relates to a combustion chamber according to the preamble of the claim 1.
  • the combustion chambers of gas turbine plants are made using a number of burners with liquid and / or gaseous fuel and with atomizing air provided.
  • the burners are often arranged in a burner hood, which the Space around the burner, which closes the so-called plenum to the outside.
  • the Plenum is arranged upstream of the combustion chamber and with the combustion chamber wall connected.
  • the air required for combustion is supplied by the compressor Gas turbine system delivered.
  • the main air flow is initially used for cooling the combustion chamber wall and used in cooling channels on the outside Passed along the combustion chamber wall.
  • the cooling channels open into the plenum. Of from there, the air preheated in the cooling channels reaches as combustion air over the burner into the combustion chamber and is finally together with the used fuel burned.
  • the combustion air entering the burner hood a defined flow structure can be impressed.
  • Cooling air and combustion air quantities partly clearly different from each other. Because very large amounts of air are required for combustion, in addition to Cooling air sends a corresponding amount of air from the compressor air flow directly into the Burner hood directed. So that this so-called bypass air also enters the plenum suitable openings are formed in the burner hood, as shown for example in DE 195 16 798 A1.
  • the temperature design of the gas turbine and the one used Fuel can be used for combustion in the combustion chamber and for cooling the air requirement required in the combustion chamber can be very different. Therefore it is necessary that the amount of bypass air can be varied. Despite one changed mass flow of the bypass air, however, the flow conditions not be disturbed in the burner hood. Otherwise, i.e. with unfavorable Inflow ratios of the bypass air result in eddies, backflow zones and other such phenomena, which negatively affect the main air flow and whose stability can affect.
  • the invention tries to avoid all these disadvantages. You have the task to create a combustion chamber with an improved air supply, which also with different mass flows of cooling and combustion air an optimal burner flow guaranteed.
  • the at least one cooling channel into that Plenum lengthened and formed there as a diffuser with an opening into the plenum is.
  • the at least one opening of the burner hood is in the area of the Diffuser or immediately downstream of its confluence. Downstream everyone The opening of the burner hood closes a separate bypass duct with a junction to the plenary.
  • the confluence of each bypass channel is opposite that Mouth of the diffuser outwardly staggered and at least aligned approximately parallel to its confluence. Every bypass channel is equipped with a pressure regulator for the bypass air.
  • bypass air is not only parallel to the main air flow but also as a so-called wall jet directly introduced into the plenum on the inner wall of the burner hood. Consequently flow separations can be countered effectively.
  • the in the bypass channels attached pressure regulating devices advantageously lead to a Adjustment of the pressure ratios of the secondary air flow (bypass air) to the in of the main air flow prevailing pressure conditions.
  • the diffuser ensures a reduction the flow rate and for maximum pressure recovery the main air flow. If no bypass air is required, they work Junctions of the bypass channels as steps and form a so-called step diffuser, at the end of which a defined separation point is created. So that will the risk of an undefined, i.e. Avoid localized detachment in the diffuser.
  • At least one further opening in is particularly advantageous downstream of each opening the burner hood.
  • each further opening Analogous to the openings arranged upstream each further opening has a bypass channel arranged downstream with a junction in the plenary.
  • Each of these bypass channels also has a pressure regulating device on.
  • the channel height of each individual bypass channel is thus successful to adapt to an optimal diffuser operation.
  • the confluence of the Bypass channels arranged one behind the other in the direction of the main air flow Openings are staggered and at least approximately parallel to each other arranged. This double stage leads to the required alignment of the bypass air. Because the release areas in the step wake of smaller steps accordingly are smaller, several small stages result in less pressure loss as one big step.
  • the pressure regulating devices act as honeycombs are formed and arranged in the slots on the air inlet side. With help of the honeycomb body, the bypass air is aligned and even so that a defined flow to the plenum can be achieved.
  • the secondary air flow can be adjusted accordingly the general operating conditions of the combustion chamber Speed and pressure ratios of the main air flow can be adjusted.
  • the honeycomb can be replaced during inspection and downtimes. so that these pressure regulators also respond to changing operating conditions are customizable.
  • At least on the most downstream Honeycomb is attached to a bracket for a honeycomb cover. By the assembly of the honeycomb cover, which also takes place when the machine is at a standstill the honeycomb can be closed and thus advantageously also on a larger one Cooling air needs to be responded to.
  • the pressure regulating device consists of a die Opening-closing blocking plate with at least one, penetrating the latter Impact hole and from one arranged in the interior of the bypass channel Impact surface.
  • the baffle holes When operating the combustion chamber, they bounce through the baffle holes rays of the secondary air flow penetrating into the plenum initially on the Impact surfaces, whereby the desired pressure loss is achieved.
  • At least one of the impact holes is designed to be closable and provided with a holder for a hole cover.
  • the assembly The disassembly of the perforated cover also takes place when the machine is at a standstill.
  • the inflowing Mass of bypass air adapted to the cooling requirements of the combustion chamber become.
  • it is useful if the most downstream arranged baffle hole of each locking plate can be closed so that the best possible diffuser effect for the main air flow is guaranteed.
  • At least two openings are formed in the burner hood and in an at least approximately transverse plane to the compressor air flow evenly distributed.
  • the gas turbine system for example, does not show the compressor and the gas turbine and the fuel feeds located outside the burner hood.
  • the direction of flow of the work equipment is indicated by arrows.
  • the gas turbine plant mainly consists of a compressor, a combustion chamber 1 designed as an annular combustion chamber with a Combustion chamber 2 and a combustion chamber wall 3, a gas turbine and one this connected generator.
  • a combustion chamber 1 designed as an annular combustion chamber with a Combustion chamber 2 and a combustion chamber wall 3, a gas turbine and one this connected generator.
  • the combustion chamber 2 of the annular combustion chamber 1 are numerous, fixed in a burner hood 4, serving the fuel supply and connected as a cone burner 5 connected. Every cone burner 5 on the upstream side consists of a swirl generator 6 and a seamlessly connecting mixing section 7 opening into combustion chamber 2.
  • EP 07 04 657 A2 known and accordingly trained cone burner 5 also referred to as a tube burner due to its tubular mixing section 7. she are each via a only schematically shown burner lance 8 from outside the burner hood 4 is supplied with fuel 9.
  • Burners are used.
  • Cooling channels 10 are arranged outside the combustion chamber 2 and encasing them, in which to burn the fuel 9 in the annular combustion chamber 1 required combustion air is brought in by the compressor.
  • the first to Cooling the combustion chamber wall 3 used combustion air forms a uniform Main air flow 11, which via openings 12 of the cooling channels 10 in a space 13 formed within the burner hood 4, the so-called Plenum of the cone burner 5, is initiated.
  • the cooling channels 10 to in the plenum 13 is extended and formed as a diffuser 14 within the plenum 13, so that the mouths 12 of the cooling channels 10 with those of the diffusers 14 coincide.
  • the bypass channels are on the air inlet side 16, 16 'pressure regulating devices 18 designed as honeycombs, 18 'arranged.
  • the combs 18, 18 ' are on both sides of the burner hood 4 a bracket 19 for a honeycomb cover 26 shown in dashed lines and thus formed closable (Fig. 2).
  • the honeycomb covers 26 can also be welded on.
  • the pressure regulating devices are 18, 18 'each as a combination of two rows in one die Slits 15, 15 'closing blocking plate 21, 21' baffle holes arranged 22, 22 ', each with a slot 15, 15' arranged inside the bypass channel 16, 16 ' Impact surface 23, 23 'is formed.
  • the baffle holes 22, 22 ' are over the distributed over the entire circumference of the locking plate 21, 21 '.
  • the one on one side of the burner hood 4, upstream slot 15 has a first impact surface 23 and that formed on the same side of the burner hood 4, downstream Slot 15 'a second impact surface 23'. Both impact surfaces 23, 23 'and the burner hood 4 arranged downstream are in the direction of the main air flow 11 graduated.
  • the impingement holes 22, 22 ' are on both sides of the burner hood 4 designed to be closable and with a holder 24 for a dashed line hole cover 27 shown provided.
  • one or several rows of baffles are closed, with those arranged downstream Bump hole rows is started.
  • the other adjustment of the secondary air flow 20 to the main air flow 11 takes place analogously to the first embodiment.
  • the outer slot 15 'of the so-called Double stage are blocked (Fig. 2, only partially shown in Fig. 3).
  • the inner slot 15 keeps the secondary air flow 20 to the required extent upright, while the outer slot 15 'acts as a stepped diffuser. If no Bypass air 20 is required, both slots 15, 15 'can also be closed, creating a two-stage diffuser (not shown). With one Diffuser can achieve a greater pressure gain than with a single, big stage. A corresponding separation distance between the two slots 15, 15 'ensures that no backflow occurs in the diffuser 14.

Claims (10)

  1. Chambre de combustion avec un plénum (13) limité vers l'extérieur par une coiffe de brûleur (4) pour recevoir au moins un écoulement d'air principal (11), avec au moins un brûleur (5) placé dans le plénum (13), une zone de combustion (2) située en aval du plénum (13), au moins un canal de refroidissement (10) enveloppant la zone de combustion (2) et débouchant dans le plénum (13) et avec au moins une ouverture (15, 15') pratiquée dans la coiffe de brûleur (4) pour un écoulement d'air secondaire (20), dans laquelle :
    ledit au moins un canal de refroidissement (10) est prolongé jusque dans le plénum (13) et a la forme, à l'intérieur du plénum (13), d'un diffuseur (14) avec une embouchure (12) dans le plénum (13) ;
    au moins une ouverture (15, 15') dans la coiffe de brûleur (4) se trouve dans la zone du diffuseur (14) ou juste en aval de son embouchure (12) et
    en aval de chaque ouverture (15, 15'), un canal de dérivation (16, 16') aboutit au plénum (13) par une embouchure (17, 17'),
    caractérisée en ce que
    a) l'embouchure (17, 17') de chaque canal de dérivation (16, 16') est au moins approximativement parallèle et échelonnée en gradins vers l'extérieur par rapport à l'embouchure (12) du diffuseur (14),
    b) chaque canal de dérivation (16, 16') est équipé d'un dispositif de régulation de pression (18, 18').
  2. Chambre de combustion selon la revendication 1, caractérisée en ce qu'en aval de chaque ouverture (15), au moins une autre ouverture (15') est pratiquée dans la coiffe de brûleur (4), chaque autre ouverture (15') dispose d'un canal de dérivation (16') disposé en aval avec une embouchure (17') dans le plénum (13), chaque canal de dérivation (16') présente un dispositif de régulation de pression (18') et en ce que les embouchures (17, 17') des canaux de dérivation (16, 16') sont échelonnées par gradins et disposées au moins approximativement parallèlement l'une par rapport à l'autre.
  3. Chambre de combustion selon la revendication 1 ou 2, caractérisée en ce que les dispositifs de régulation de pression (18, 18') sont en forme de nids d'abeilles.
  4. Chambre de combustion selon la revendication 3, caractérisée en ce que les nids d'abeilles (18, 18') sont disposés du côté d'entrée d'air dans les canaux de dérivation (16, 16').
  5. Chambre de combustion selon la revendication 3, caractérisée en ce qu'au moins un des nids d'abeilles (18, 18') peut être obturé.
  6. Chambre de combustion selon la revendication 5, caractérisée en ce qu'au moins le nid d'abeilles (18') se trouvant le plus en aval est équipé d'une fixation (19) pour le recouvrement du nid d'abeilles (26).
  7. Chambre de combustion selon la revendication 1 ou 2, caractérisée en ce que chaque dispositif de régulation de pression (18, 18') se compose d'une plaque de fermeture (21, 21') obturant l'ouverture (15, 15') avec au moins un trou de surface formant chicane (22, 22') traversant cette plaque et d'une surface formant chicane (23, 23') disposée à l'intérieur du canal de dérivation (16, 16').
  8. Chambre de combustion selon la revendication 7, caractérisée en ce qu'au moins un des trous de surface formant chicane (22, 22') de chaque dispositif de régulation de pression (18, 18') peut être obturé.
  9. Chambre de combustion selon la revendication 8, caractérisée en ce que le trou de surface formant chicane (22, 22') de chaque plaque de fermeture (21, 21') se trouvant le plus en aval est équipé d'une fixation (24) pour un recouvrement du trou (27).
  10. Chambre de combustion selon une des revendications 1 à 9, caractérisée en ce qu'au moins deux ouvertures (15, 15') sont pratiquées à chaque fois dans la coiffe de brûleur (4) et sont réparties uniformément dans un plan au moins approximativement transversal à l'écoulement d'air principal (11).
EP98810304A 1997-05-17 1998-04-09 Chambre de combustion Expired - Lifetime EP0882932B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19720786 1997-05-17
DE19720786A DE19720786A1 (de) 1997-05-17 1997-05-17 Brennkammer

Publications (3)

Publication Number Publication Date
EP0882932A2 EP0882932A2 (fr) 1998-12-09
EP0882932A3 EP0882932A3 (fr) 2000-03-22
EP0882932B1 true EP0882932B1 (fr) 2003-03-12

Family

ID=7829802

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98810304A Expired - Lifetime EP0882932B1 (fr) 1997-05-17 1998-04-09 Chambre de combustion

Country Status (5)

Country Link
US (1) US6106278A (fr)
EP (1) EP0882932B1 (fr)
JP (1) JP4036962B2 (fr)
CN (1) CN1114787C (fr)
DE (2) DE19720786A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19829398A1 (de) * 1998-07-01 2000-01-05 Asea Brown Boveri Gasturbine
DE19900025A1 (de) * 1999-01-02 2000-07-06 Abb Research Ltd Brennerhaube
DE10064259B4 (de) * 2000-12-22 2012-02-02 Alstom Technology Ltd. Brenner mit hoher Flammenstabilität
US6889523B2 (en) * 2003-03-07 2005-05-10 Elkcorp LNG production in cryogenic natural gas processing plants
US20050076644A1 (en) * 2003-10-08 2005-04-14 Hardwicke Canan Uslu Quiet combustor for a gas turbine engine
US7273366B1 (en) * 2003-10-28 2007-09-25 Soil-Therm Equipment, Inc. Method and apparatus for destruction of vapors and waste streams
US7270539B1 (en) * 2003-10-28 2007-09-18 Soil-Therm Equipment, Inc. Method and apparatus for destruction of vapors and waste streams using flash oxidation
US20160102857A1 (en) * 2014-10-13 2016-04-14 Eclipse, Inc. Swirl jet burner
KR101596715B1 (ko) * 2014-11-25 2016-02-23 주식회사 경동나비엔 연소실 냉각 구조를 갖는 연소장치

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FR1430185A (fr) * 1964-12-23 1966-03-04 Foyer de combustion à fentes tourbillonnaires
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DE2728399C2 (de) * 1977-06-24 1982-04-22 Brown, Boveri & Cie Ag, 6800 Mannheim Brennkammer für eine Gasturbine
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DE19523094A1 (de) 1995-06-26 1997-01-02 Abb Management Ag Brennkammer

Also Published As

Publication number Publication date
CN1114787C (zh) 2003-07-16
JPH10325542A (ja) 1998-12-08
DE19720786A1 (de) 1998-11-19
JP4036962B2 (ja) 2008-01-23
US6106278A (en) 2000-08-22
CN1199837A (zh) 1998-11-25
EP0882932A3 (fr) 2000-03-22
DE59807433D1 (de) 2003-04-17
EP0882932A2 (fr) 1998-12-09

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