EP0718558B1 - Brûleur - Google Patents

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Publication number
EP0718558B1
EP0718558B1 EP95810761A EP95810761A EP0718558B1 EP 0718558 B1 EP0718558 B1 EP 0718558B1 EP 95810761 A EP95810761 A EP 95810761A EP 95810761 A EP95810761 A EP 95810761A EP 0718558 B1 EP0718558 B1 EP 0718558B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
fuel
flow
vortex
combustion
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
EP95810761A
Other languages
German (de)
English (en)
Other versions
EP0718558A3 (fr
EP0718558A2 (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.)
General Electric Switzerland GmbH
ABB Asea Brown Boveri Ltd
Original Assignee
ABB 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 ABB Schweiz AG filed Critical ABB Schweiz AG
Publication of EP0718558A2 publication Critical patent/EP0718558A2/fr
Publication of EP0718558A3 publication Critical patent/EP0718558A3/fr
Application granted granted Critical
Publication of EP0718558B1 publication Critical patent/EP0718558B1/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
    • F23D23/00—Assemblies of two or more burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M9/00—Baffles or deflectors for air or combustion products; Flame shields
    • F23M9/02—Baffles or deflectors for air or combustion products; Flame shields in air inlets
    • 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
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners

Definitions

  • the present invention relates to a combustion chamber according to Preamble of claim 1. It also concerns a Method for operating a gas turbine group with a such combustion chamber.
  • the principle of mixture formation is based on in a combustion air flow by means of a Inflow channel arranged vortex generators to vortex generate, and by means of the vortex generators arranged fuel lances a fuel in the to introduce swirled combustion air flow.
  • swirled combustion air flow finds an intense Mixing the fuel with the combustion air instead, so that an intensely and evenly premixed Mixture available for low-emission combustion stands.
  • temperatures are aimed at, which have a certain safety margin against extinguishing the flame, whereby the The blades themselves are subjected to a higher temperature than is the case with conventional combustion chambers is.
  • the invention seeks to remedy this.
  • the invention as it is characterized in the claims, the Task based on a combustion chamber of the beginning mentioned type within the hot gas flow To accomplish temperature gradation.
  • a temperature gradation within the hot gas flow leaves preferably achieved in an annular combustion chamber the fuel over a number in the circumferential direction of the Ring combustion chamber acting fuel lances is injected.
  • Each of these fuel lances has several different ones directed nozzles through which the fuel in the Flow cross section of the annular combustion chamber introduced with which a sectorial enrichment of the Firing mixture is reached.
  • Such a configuration is excellently suited, a sectorally different Enrichment of the fuel mixture to accomplish the injected fuel is mainly distributed within the sector assigned to it, which makes it possible to over the temperature distribution to influence the fuel mixing. So that becomes a Temperature gradation reached in the radial direction, which the Representing profile flow for the blades to be loaded.
  • Vortex generators which are placed upstream of the fuel lances.
  • An essential one The advantage of this arrangement is that the Vortex generators according to sector, according to the fuel injection be arranged, and there also an individual Can produce effect.
  • Another important advantage of the invention is in that the temperature gradation is targeted in the radial direction can be customized.
  • the introduction is preferred of the fuel handled so that the scoop feet relieved at a given average temperature of the hot gases become.
  • the temperature of the hot gases is in the range the blade feet lower than the average temperature, this loss can easily be compensated by along the much larger area of the rest of the blade profile a slightly higher temperature of the hot gases becomes.
  • the caloric load in the area decreases the weak points, so the cooling of the blading reduce accordingly what ultimately turns into a Efficiency improvement reflected.
  • the turbine inlet temperature can be the same for the same service life be increased accordingly, leading to an increase in the efficiency and performance of the machine leads.
  • Another advantage of the invention is that by targeted temperature grading, especially in the transients Load ranges a better transient behavior of the rotor is what leads to smaller games between the Stator and the rotating parts leads.
  • annular combustion chamber 1 shows, as can be seen from the shaft axis 10, an annular combustion chamber 1, which is essentially in the form of a contiguous annular or quasi-annular cylinder occupies.
  • a combustion chamber also consist of only one cylinder.
  • Fig. 1 shows only the significant part of the Annular combustion chamber 1, namely the vortex formation that leads to a Fuel lance with temperature gradation and downstream located and to be applied turbine.
  • the main flow 4 is always a combustion air flow, its temperature and Composition can be very different.
  • the combustion air 4 is caused by the vortex generators 200 twists that in the subsequent premixing and firing zone 5a no more recirculation areas in the wake of the vortex generators 200 occur.
  • this premixing and firing zone 5a are several fuel lances 3 disposes of the supply of a fuel 11 and a supporting air 12 take over.
  • the feeder this media 11, 12 to the individual fuel lances 3 can accomplished, for example, by a ring line, not shown become.
  • the one from the vortex generators 200 triggered swirl flow is injected with the sector Fuel 7a, 7b in operative connection, such that by a corresponding regulation of the amount of fuel over the individual Sectors a different size of the individual resulting from the action of the vortex generators 200 Partial flows of the combustion air 4 results in the subsequent combustion a different temperature profile triggers.
  • a temperature gradation 8 over the flow cross section is graphical in the figure and represented qualitatively. How easy to deduce from this presentation is applied to this temperature-graded hot gas front the blades via corresponding guide vanes 9 a turbine 2. According to the temperature gradation 8 the shovel feet are calorically less stressed, but the the remaining blade surface is exposed to a slightly higher temperature, so that's for efficiency and performance the relevant mean hot gas temperature is maintained.
  • Fig. 2 shows, for each fuel lance 3 in the area Vortex generators 200 one for an annular annulus combustion chamber 1 typical chamber formed, which also includes lateral vortex generators 200 can be attached.
  • the sectoral fuel injection 7a, 7b depends on the position of those placed upstream Vortex generators 200, this injection to ensure a temperature grading preferably between the individual To align flank surfaces of the vortex generators 200 so that the turbulence that arises there is a good mixture with the appropriate amount of fuel.
  • the fuel injection 7a, 7b can also Carry out over a large number of nozzles, depending on for the desired temperature grading and depending to the location of the individual vortex generators 200 within the flow cross-section of the annular combustion chamber 1.
  • This annular combustion chamber can have several radial extensions superordinate rows of chambers exist, one row of chambers of which as a pilot stage to the others concentrically arranged Rows of chambers can be designed.
  • a vortex generator 200, 201, 202 essentially consists of three freely flowing triangular surfaces. These are a roof surface 210 and two side surfaces 211 and 213. In their longitudinal extension, these surfaces run at certain angles in the direction of flow.
  • the side walls of the vortex generators 200, 201, 202, which preferably consist of right-angled triangles, are fixed with their long sides on the channel wall 6 already mentioned, preferably gas-tight. They are oriented so that they form a joint on their narrow sides, including the arrow angle ⁇ .
  • the joint is designed as a sharp connecting edge 216 and is perpendicular to each channel wall 6 with which the side surfaces are flush.
  • the two side surfaces 211, 213 including the arrow angle ⁇ are symmetrical in shape, size and orientation in FIG. 3, they are arranged on both sides of an axis of symmetry 217 which is aligned in the same direction as the channel axis.
  • the roof surface 210 lies against the same channel wall 6 as the side surfaces 211, 213 with a very narrow edge 215 running transversely to the flow channel.
  • Its longitudinal edges 212, 214 are flush with the longitudinal edges of the side surfaces 211, 213 which protrude into the flow channel.
  • the vortex generator 200, 201, 202 can also be provided with a bottom surface with which it is attached to the channel wall 6 in a suitable manner. Such a floor area is, however, unrelated to the mode of operation of the element.
  • the mode of operation of the vortex generator 200, 201, 202 is the following: When flowing around edges 212 and 214, the Main flow converted into a pair of counter-rotating vortices, as schematically sketched in the figures.
  • the Vortex axes lie in the axis of the main flow.
  • the vortex strength or the number of twists increases, and the location of the vortex burst shifts upstream into the area of the vortex generator 200, 201, 202 themselves.
  • these are both angles e and ⁇ due to structural conditions and determined by the process itself. Need to be adjusted these vortex generators only in terms of length and height, as detailed below under Fig. 6 for execution will arrive.
  • the connecting edge 216 forms the two side surfaces 211, 213 the downstream edge of the vortex generator 200.
  • the one running across the canal Edge 215 of roof surface 210 is thus that of the channel flow edge applied first.
  • Vortex generator 201 is a so-called half "vortex generator" the base of a vortex generator shown in FIG. 6.
  • Vortex generator 201 shown here is only one of the two Provide side surfaces with the arrow angle ⁇ / 2.
  • the other Side surface is straight and aligned in the direction of flow.
  • a vortex on the swept side is created here, like this is symbolized in the figure. Accordingly, it is downstream this vortex generator does not have a vortex-neutral field, but instead a swirl is imposed on the current.
  • Fig. 5 differs from Fig. 3 in so far as here the sharp connecting edge 216 of the vortex generator 202 is the point which is affected first by the channel flow becomes. The element is therefore rotated by 180 °. How it can be seen from the illustration that the two have opposite directions Vortex changed their sense of rotation.
  • Fig. 6 shows the basic geometry of one in a channel 5 built-in vortex generator 200.
  • the influence on the ratio to be chosen of the two heights h / H is the pressure drop, that occurs when the vortex generator 200 flows around. It it goes without saying that with a larger ratio h / H the Pressure loss coefficient increases.
  • the vortex generators 200, 201, 202 are mainly used when it comes to two currents with each other to mix.
  • the main flow 4 for example as Hot gases, attacks the transverse one in the direction of the arrow Edge 215, or respectively the connecting edge 216.
  • the secondary flow in the form of a gaseous and / or liquid fuel, which is enriched with a portion of supporting air at most (See Fig. 1) has a much smaller one Mass flow as the main flow. This secondary flow is in the present case downstream of the vortex generator the main flow is initiated, as shown in FIG. 1 in particular emerges well.
  • the vortex generators 200 spaced around the circumference of a chamber of the channel 5 distributed.
  • the vortex generators are also strung together in the circumferential direction, that no gaps are left on the channel wall 6.
  • Figures 7-13 show other possible forms of introduction of fuel in the main flow 4. These variants can interact with each other and with a central Fuel injection, such as that shown in FIG. 1 emerges can be combined.
  • the fuel in addition to channel wall bores 220, which are located downstream of the vortex generators, also injected via wall holes 221, which are immediately next to the side surfaces 211, 213 and in their Longitudinal extension in the same channel wall 6 are located on the the vortex generators are arranged.
  • the introduction of the Fuel through the wall holes 221 gives the generated Whirl an extra impulse, which is the lifespan of the vortex generator extended.
  • the fuel is fed through a slot 222 or injected via wall holes 223, both precautions immediately in front of the cross-canal extending edge 215 of the roof surface 210 and in the Longitudinal extension in the same channel wall 6 are located on the the vortex generators are arranged.
  • the geometry of the Wall bores 223 or the slot 222 is selected such that the fuel at a certain injection angle into the Main flow 4 is entered and the re-placed vortex generator as a protective film against the hot main flow 4 largely shielded by flow.
  • the secondary flow (See above) first of all via guides not shown through the channel wall 6 into the hollow interior of the vortex generators initiated. In this way, an internal cooling facility for the vortex generators created.
  • the fuel is injected via wall bores 224, which is located directly within the roof area 210 behind and along the one running across the channel Edge 215.
  • the vortex generator is cooled here more external than internal.
  • the emerging secondary flow forms a flow against the roof surface 210 against the hot main flow 4 shielding protective layer.
  • the fuel is injected via wall bores 225, which within the roof surface 210 along the line of symmetry 217 are staggered.
  • the channel walls 6 are particularly good before the hot main flow 4 protected because the fuel is initially on the outer circumference the vertebra is introduced.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Claims (10)

  1. Chambre de combustion, qui se compose essentiellement d'un canal d'admission (5) conduisant un air de combustion (4) et d'une zone de prémélange et de combustion qui suit (5a), dans laquelle un certain nombre de générateurs de tourbillon (200, 201, 202) sont disposés dans le canal d'admission (5), et dans laquelle au moins une lance à combustible (3) est disposée en aval des générateurs de tourbillon pour l'injection d'un combustible (11) dans l'air de combustion, caractérisée en ce que la quantité de combustible (11) injectée par la lance à combustible (3) est étagée par la lance à combustible (3) en fonction de la direction d'injection (7a, 7b), d'une façon telle que les gaz chauds provenant d'une combustion du combustible présentent un profil de température (8) étagé sur la section transversale de passage de la chambre de combustion (1).
  2. Chambre de combustion suivant la revendication 1, caractérisée en ce que la chambre de combustion (1) est une chambre de combustion annulaire.
  3. Chambre de combustion suivant la revendication 1, caractérisée en ce qu'un générateur de tourbillon (200) présente trois faces librement balayées, qui s'étendent dans le sens de l'écoulement, faces dont l'une forme la face de toit (210) et les deux autres forment les faces latérales (211, 213), en ce que les faces latérales (211, 213) sont jointives avec un même segment de paroi du canal d'admission (5) et définissent l'une avec l'autre l'angle de flèche (α), en ce que la face de toit (210) s'applique par une arête (215) orientée transversalement au canal d'admission (5) sur le même segment de paroi de la paroi de canal (6) que les faces latérales (211, 213), et en ce que des arêtes longitudinales (212, 214) de la face de toit (210) sont jointives avec les arêtes longitudinales des faces latérales (211, 213) en saillie dans le canal d'admission (5) et sont orientées sous un angle d'incidence () par rapport au segment de paroi du canal d'admission (5).
  4. Chambre de combustion suivant la revendication 3, caractérisée en ce que les deux faces latérales (211, 213) du générateur de tourbillon (200) définissant l'angle de flèche (α) sont disposées symétriquement par rapport à un axe de symétrie (217).
  5. Chambre de combustion suivant la revendication 3, caractérisée en ce que les deux faces latérales (211, 213) définissant l'angle de flèche (α, α/2) comprennent une arête de jonction l'une à l'autre (216), qui forme avec les arêtes longitudinales (212, 214) de la face de toit (210) une pointe (218), et en ce que l'arête de jonction (216) se trouve en position radiale par rapport au canal d'admission circulaire (5).
  6. Chambre de combustion suivant la revendication 5, caractérisée en ce que l'arête de jonction (216) et/ou les arêtes longitudinales (212, 214) de la face de toit (210) est/sont au moins approximativement une/des arête(s) vive(s).
  7. Chambre de combustion suivant l'une des revendications 4 ou 5, caractérisée en ce que l'axe de symétrie (217) du générateur de tourbillon (200) est parallèle à l'axe du canal, en ce que l'arête de jonction (216) des deux faces latérales (211, 213) forme l'arête aval du générateur de tourbillon (200), et en ce que l'arête (215) de la face de toit (210) orientée transversalement au canal parcouru (5) est l'arête atteinte en premier lieu par l'écoulement principal (4).
  8. Chambre de combustion suivant la revendication 1, caractérisée en ce que le rapport de la hauteur (h) du générateur de tourbillon (200) à la hauteur (H) du canal d'admission (5) est choisie d'une façon telle qu'un tourbillon produit remplisse, immédiatement en aval du générateur de tourbillon (200), toute la hauteur (H) du canal d'admission (5) et toute la hauteur (h) de la partie du canal associée au générateur de tourbillon (200).
  9. Procédé pour la conduite d'un turbogroupe à gaz avec une chambre de combustion suivant la revendication 1, qui se compose essentiellement d'un canal d'admission (5) et d'une zone de prémélange et de combustion (5a) qui suit le canal d'admission, dans lequel la chambre de combustion (1) est disposée entre deux turbomachines dans le sens de l'écoulement, caractérisé en ce qu'un air de combustion (4) provenant de la turbomachine disposée en amont est conduit sur des générateurs de tourbillon (200, 201, 202), en ce que cet air de combustion (4) est mélangé à un combustible (11) du côté aval des générateurs de tourbillon, en ce que l'injection (7a, 7b) du combustible (11) est effectuée en direction et en quantité différente dans la zone de prémélange et de combustion (5a), de sorte que les gaz chauds nés de la combustion de ce mélange forment un front de température étagé (8), dont la température minimale correspond dans l'écoulement à la base des aubes à actionner de la turbomachine (2) qui suit.
  10. Procédé suivant la revendication 9, caractérisé en ce que le combustible (11) est soutenu par un air d'appoint (12).
EP95810761A 1994-12-24 1995-12-05 Brûleur Expired - Lifetime EP0718558B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4446611A DE4446611A1 (de) 1994-12-24 1994-12-24 Brennkammer
DE4446611 1994-12-24

Publications (3)

Publication Number Publication Date
EP0718558A2 EP0718558A2 (fr) 1996-06-26
EP0718558A3 EP0718558A3 (fr) 1997-04-23
EP0718558B1 true EP0718558B1 (fr) 2001-04-18

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Application Number Title Priority Date Filing Date
EP95810761A Expired - Lifetime EP0718558B1 (fr) 1994-12-24 1995-12-05 Brûleur

Country Status (5)

Country Link
US (1) US5609030A (fr)
EP (1) EP0718558B1 (fr)
JP (1) JP3977454B2 (fr)
CN (1) CN1076786C (fr)
DE (2) DE4446611A1 (fr)

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WO2009109454A1 (fr) 2008-03-07 2009-09-11 Alstom Technology Ltd Procédé et ensemble brûleur servant à produire du gaz chaud et utilisation dudit procédé
EP2252831B1 (fr) 2008-03-07 2013-05-08 Alstom Technology Ltd Ensemble brûleur et son utilisation
EP2112433A1 (fr) * 2008-04-23 2009-10-28 Siemens Aktiengesellschaft Chambre de mélange
ES2400247T3 (es) * 2008-12-19 2013-04-08 Alstom Technology Ltd Quemador de una turbina de gas que tiene una configuración de lanza especial
EP2230455B1 (fr) 2009-03-16 2012-04-18 Alstom Technology Ltd Brûleur pour une turbine à gaz et procédé de refroidissement local d'un flux de gaz chauds passant par un brûleur
EP2253888B1 (fr) * 2009-05-14 2013-10-16 Alstom Technology Ltd Brûleur d'une turbine à gaz ayant un générateur de vortex avec une lance à combustible
WO2013139914A1 (fr) * 2012-03-23 2013-09-26 Alstom Technology Ltd Dispositif de combustion
EP2644997A1 (fr) 2012-03-26 2013-10-02 Alstom Technology Ltd Agencement de mélange pour mélanger un combustible avec un flux de gaz contenant de l'oxygène
DE102012213852A1 (de) * 2012-08-06 2014-02-06 Siemens Aktiengesellschaft Lokale Verbesserung der Mischung von Luft und Brennstoff in Brennern mit Drallerzeugern
EP2775107A1 (fr) 2013-03-06 2014-09-10 Alstom Technology Ltd Procédé pour démarrer une centrale électrique à cycle combiné
EP2789915A1 (fr) * 2013-04-10 2014-10-15 Alstom Technology Ltd Procédé de fonctionnement d'une chambre de combustion et chambre de combustion
EP2894405B1 (fr) * 2014-01-10 2016-11-23 General Electric Technology GmbH Dispositif à combustion séquentielle avec un gaz de dilution
WO2016032434A1 (fr) 2014-08-26 2016-03-03 Siemens Energy, Inc. Agencement de trous de refroidissement de film pour résonateurs acoustiques dans des moteurs à turbine à gaz
EP3081862B1 (fr) 2015-04-13 2020-08-19 Ansaldo Energia Switzerland AG Agencement de génération de vortex pour un brûleur à pré-mélange d'une turbine à gaz et turbine à gaz avec un tel agencement de génération de vortex
US11384937B1 (en) * 2021-05-12 2022-07-12 General Electric Company Swirler with integrated damper
US11454396B1 (en) * 2021-06-07 2022-09-27 General Electric Company Fuel injector and pre-mixer system for a burner array

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EP0620362A1 (fr) * 1993-04-08 1994-10-19 ABB Management AG Turbine à gaz

Also Published As

Publication number Publication date
CN1076786C (zh) 2001-12-26
CN1130718A (zh) 1996-09-11
JP3977454B2 (ja) 2007-09-19
EP0718558A3 (fr) 1997-04-23
DE4446611A1 (de) 1996-06-27
US5609030A (en) 1997-03-11
JPH08226647A (ja) 1996-09-03
EP0718558A2 (fr) 1996-06-26
DE59509206D1 (de) 2001-05-23

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