EP0687860A2 - Chambre de combustion à allumage automatique - Google Patents

Chambre de combustion à allumage automatique Download PDF

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Publication number
EP0687860A2
EP0687860A2 EP95810291A EP95810291A EP0687860A2 EP 0687860 A2 EP0687860 A2 EP 0687860A2 EP 95810291 A EP95810291 A EP 95810291A EP 95810291 A EP95810291 A EP 95810291A EP 0687860 A2 EP0687860 A2 EP 0687860A2
Authority
EP
European Patent Office
Prior art keywords
channel
combustion chamber
zone
fuel
flow
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
EP95810291A
Other languages
German (de)
English (en)
Other versions
EP0687860B1 (fr
EP0687860A3 (fr
Inventor
Rolf Dr. Althaus
Yau-Pin Dr. Chyou
Franz Joos
Jakob J. Prof. Dr. Keller
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 Management 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 Management AG filed Critical ABB Management AG
Publication of EP0687860A2 publication Critical patent/EP0687860A2/fr
Publication of EP0687860A3 publication Critical patent/EP0687860A3/fr
Application granted granted Critical
Publication of EP0687860B1 publication Critical patent/EP0687860B1/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
    • 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
    • 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
    • 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
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/12—Fluid guiding means, e.g. vanes
    • F05B2240/122—Vortex generators, turbulators, or the like, for mixing
    • 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 the preamble of claim 1.
  • high NOx emissions must always be expected, the emissions of which are no longer in line with the newer legislation of the most important countries in terms of market;
  • a flashback from the flame zone into the interior of the premixing section is still possible, in particular along the inner wall, where naturally a relatively low flow velocity of the combustion air prevails.
  • a typical firing system in which the above-mentioned techniques have to fail against a flashback, concerns a combustion chamber designed for self-ignition.
  • This is usually a largely cylindrical tube or an annular combustion chamber, in which a working gas flows in at a relatively high temperature, where it forms a mixture with an injected fuel, the fuel triggering self-ignition.
  • the caloric treatment of the working gas into hot gas takes place solely within this tube or this annular combustion chamber.
  • it is an afterburning chamber that acts between a high-pressure and low-pressure turbine, it is impossible for reasons of space to install premix burners or to provide aids against a flashback, which is why until now this combustion technology, which was attractive in itself, had to be dispensed with.
  • the postulate is to provide an annular combustion chamber as an afterburning chamber of a gas turbine group mounted on a shaft, additional problems arise with regard to minimizing the length of this combustion chamber, which are connected with flame stabilization.
  • the invention seeks to remedy this.
  • the invention as characterized in the claims, is the object to propose measures for a combustion chamber of the type mentioned at the outset which induce flame stabilization and minimize pollutant emissions.
  • a fuel is introduced into these large swirl structures.
  • a fuel lance protruding into the channel is suitable for this.
  • An important advantage of the invention is that the swirl flow originating from the vortex generators on the one hand ensures a large-scale distribution of the introduced fuel, and on the other hand this turbulence causes a homogenization in the mixture formation of combustion air with fuel.
  • premixed fuel / air mixtures generally tend to self-ignite, and therefore to flashback.
  • the advantage of the invention can be seen here in that the fuel is injected behind a narrowing point in the premixing channel. This constriction has the advantage that the turbulence is reduced by increasing the axial speed, which minimizes the risk of a flashback due to the change in the turbulent flame speed.
  • the axial component is reduced again by the opening taking place there: the advantage of this can be seen in the fact that the increasing turbulence ensures homogeneous mixing.
  • a cross-sectional expansion takes place, the size of which gives the actual flow cross-section of the combustion chamber or the combustion zone.
  • marginal zones are formed during operation, in which vortex detachments, i.e. Vortex rings arise, which in turn lead to a stabilization of the flame front.
  • This configuration is particularly advantageous where the combustion chamber is designed for self-ignition.
  • Such a combustion chamber preferably has essentially the shape of an annular or annular combustion chamber, it has a short axial length, and it is flowed through by a working gas of high temperature and high speed.
  • the peripheral vortex detachments mentioned stabilize the flame front in such a way that no additional measures are required to prevent the flame from reigniting.
  • annular combustion chamber 1 shows, as can be seen from the shaft axis 16, an annular combustion chamber 1, which essentially has the shape of a coherent annular or quasi-annular cylinder.
  • a combustion chamber can also consist of a number of axially, quasi-axially or helically arranged and individually closed combustion chambers.
  • Such ring combustion chambers are excellently suited to be operated as self-igniting combustion chambers which are placed in the flow direction between two turbines mounted on a shaft. If such an annular combustion chamber 1 is operated on self-ignition, the upstream turbine 2 is only designed for partial relaxation of the hot gases 3, so that the exhaust gases 4 downstream of this turbine 2 still flow into the inflow zone 5 of the annular combustion chamber 1 at a very high temperature.
  • This inflow zone 5 is equipped on the inside and in the circumferential direction of the channel wall 6 with a series of vortex-generating elements 100, hereinafter only called vortex generators, which will be discussed in more detail below.
  • the exhaust gases 4 are swirled by the vortex generators 100 such that no recirculation areas occur in the wake of the vortex generators 100 mentioned in the subsequent premixing section 7.
  • a plurality of fuel lances 8 are arranged, which take over the supply of a fuel 9 and supporting air 10. These fuel lances 8 are discussed in more detail below. These media can be supplied to the individual fuel lances 8, for example, via a ring line (not shown).
  • the swirl flow triggered by the vortex generators 100 provides for a large-scale distribution of the introduced fuel 9, and possibly also the admixed supporting air 10. Furthermore, the swirl flow ensures a homogenization of the mixture of combustion air and fuel.
  • the fuel 9 injected into the exhaust gases 4 by the fuel lance 8 triggers self-ignition if these exhaust gases 4 have the specific temperature which the fuel-dependent auto-ignition is capable of triggering. If the annular combustion chamber 1 is operated with a gaseous fuel, the Initiation of self-ignition a temperature of the exhaust gases 4 greater than 850 ° C is present. With such a combustion, as already appreciated above, there is a risk of a flashback.
  • premixing zone 7 as a venturi channel and, on the other hand, disposing the injection of the fuel 9 in the region of the largest constriction in the premixing zone 7.
  • the narrowing in the premixing zone 7 reduces the turbulence by increasing the axial speed, which minimizes the risk of kickback by reducing the turbulent flame speed.
  • the large-scale distribution of the fuel 9 is still guaranteed, since the peripheral component of the swirl flow originating from the vortex generators 100 is not impaired.
  • a combustion zone 11 follows the relatively short premixing zone 7. The transition between the two zones is formed by a radial cross-sectional jump 12, which initially induces the flow cross-section of the combustion zone 11.
  • the vortex generators 100 are designed such that no recirculation takes place in the premixing zone 7; only after the sudden widening of the cross section is the burst of the swirl flow desired.
  • the swirl flow supports the rapid re-application of the flow behind the cross-sectional jump 12, so that a high burn-out with a short overall length can be achieved by utilizing the volume of the combustion zone 11 as fully as possible.
  • a vortex generator 100, 101, 102 essentially consists of three freely flowing triangular surfaces. These are a roof surface 110 and two side surfaces 111 and 113. In their longitudinal extent, these surfaces run at certain angles in the direction of flow.
  • the side walls of the vortex generators 100, 101, 102 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 an arrow angle ⁇ .
  • the joint is designed as a sharp connecting edge 116 and is perpendicular to each channel wall 6 with which the side surfaces are flush.
  • the two side surfaces 111, 113 including the arrow angle ⁇ are symmetrical in shape, size and orientation in FIG. 4, they are arranged on both sides of an axis of symmetry 117 which is oriented in the same direction as the channel axis.
  • the roof surface 110 lies against the same channel wall 6 as the side surfaces 111, 113 with a very narrow edge 115 running transversely to the flow channel. Its longitudinal edges 112, 114 are flush with the longitudinal edges of the side surfaces 111 protruding into the flow channel , 113.
  • the roof surface 110 extends at an angle of attack ⁇ to the channel wall 6, the longitudinal edges 112, 114 of which, together with the connecting edge 116, form a point 118.
  • the vortex generator 100, 101, 102 can also be provided with a bottom surface with which he is suitably attached to the channel wall 6. Such a floor area is, however, unrelated to the mode of operation of the element.
  • the mode of operation of the vortex generator 100, 101, 102 is as follows: When flowing around the edges 112 and 114, the main flow is converted into a pair of opposing vortices, as is schematically outlined in the figures.
  • the vortex axes lie in the axis of the main flow.
  • the number of swirls and the location of the vortex breakdown (vortex breakdown), if the latter is aimed for, are determined by appropriate selection of the angle of attack ⁇ and the arrow angle ⁇ .
  • the vortex strength or the number of swirls is increased, and the location of the vortex bursting shifts upstream into the area of the vortex generator 100, 101, 102 itself.
  • these two angles ⁇ and ⁇ are due to structural conditions and determined by the process itself.
  • These vortex generators only have to be adapted in terms of length and height, as will be explained in more detail below under FIG. 5.
  • the connecting edge 116 of the two side surfaces 111, 113 forms the downstream edge of the vortex generator 100.
  • the edge 115 of the roof surface 110 which runs transversely to the flow through the channel is thus the edge which is first acted upon by the channel flow.
  • FIG. 3 shows a so-called half "vortex generator” based on a vortex generator according to FIG. 2.
  • the vortex generator 101 shown here only one of the two side surfaces is provided with the arrow angle ⁇ / 2.
  • the other side surface is straight and oriented in the direction of flow.
  • this vortex generator only one vortex is generated on the arrowed side, as is shown in the figure. Accordingly, it is downstream this vortex generator does not have a vortex-neutral field, but a swirl is forced on the flow.
  • FIG. 4 differs from FIG. 2 in that the sharp connecting edge 116 of the vortex generator 102 is the point which is first acted upon by the channel flow.
  • the element is rotated 180 degrees. As can be seen from the illustration, the two opposite vortices have changed their sense of rotation.
  • the height h of the connecting edge 116 will be coordinated with the channel height H, or the height of the channel part which is assigned to the vortex generator that the generated vortex immediately downstream of the vortex generator 100 already has such a size that the full channel height H is filled with it. This leads to a uniform speed distribution in the cross-section applied.
  • Another criterion that can influence the ratio of the two heights h / H to be selected is the pressure drop that occurs when the vortex generator 100 flows around. It goes without saying that the pressure loss coefficient also increases with a larger ratio h / H.
  • the vortex generators 100, 101, 102 are mainly used when it comes to mixing two flows.
  • the main flow 4 in the form of combustion air attacks the transverse edge 115 or the connecting edge 116 in the direction of the arrow.
  • the secondary flow in the form of a gaseous and / or liquid fuel, which is possibly enriched with a portion of supporting air (see FIG. 13), has a significant effect smaller mass flow than the main flow. In the present case, this secondary flow becomes downstream of the vortex generator into the main flow initiated, as can be seen particularly well from FIG. 1.
  • vortex generators 100 are spaced apart over the circumference of the channel 5.
  • the vortex generators can also be strung together in the circumferential direction so that no gaps are left on the channel wall 6.
  • the vortices to be generated are ultimately decisive for the choice of the number and the arrangement of the vortex generators.
  • FIGS. 6-12 show further possible forms of introducing the fuel into the combustion air 4. These variants can be combined in a variety of ways with one another and with a central fuel injection, as can be seen, for example, from FIG. 1.
  • the fuel in addition to channel wall bores 120, which are located downstream of the vortex generators, is also injected via wall bores 121, which are located directly next to the side surfaces 111, 113 and in their longitudinal extent in the same channel wall 6, on the the vortex generators are arranged.
  • the introduction of the fuel through the wall bores 121 gives the generated vortices an additional impulse, which extends the lifespan of the vortex generator.
  • the fuel is injected via a slot 122 or via wall bores 123, both precautions being located directly in front of the edge 115 of the roof surface 110 running transversely to the flowed channel and in its longitudinal extent in the same channel wall 6 on which the Vortex generators are arranged.
  • the geometry of the wall bores 123 or of the slot 122 is selected such that the fuel is introduced into the main flow 4 at a specific injection angle and the vortex generator that is placed behind as a protective film against the hot main flow 4 largely shielded by flow.
  • the secondary flow (cf. above) is first introduced into the hollow interior of the vortex generators via guides (not shown) through the channel wall 6. This creates an internal cooling facility for the vortex generators without providing any additional equipment.
  • the fuel is injected via wall bores 124, which are located inside the roof surface 110 directly behind and along the edge 115 running transversely to the flow channel.
  • the vortex generator is cooled here more externally than internally.
  • the emerging secondary flow forms when flowing around the roof surface 110 has a protective layer shielding it from the hot main flow 4.
  • the fuel is injected via wall bores 125, which are staggered within the roof surface 110 along the line of symmetry 117.
  • the channel walls 6 are particularly well protected from the hot main flow 4, since the fuel is first introduced on the outer circumference of the vortex.
  • the fuel is injected via wall bores 126, which are located in the longitudinal edges 112, 114 of the roof surface 110.
  • This solution ensures good cooling of the vortex generators, since the fuel escapes from its extremities and thus completely flushes the inner walls of the element.
  • the secondary flow is fed directly into the resulting vortex, which leads to defined flow conditions.
  • the injection takes place via wall bores 127, which are located in the side surfaces 111 and 113, on the one hand in the area of the longitudinal edges 112 and 114, on the other hand in the area of the connecting edge 116.
  • This variant is similar in effect to that from FIG. 6 (bores 121) and from FIG. 11 (bores 126).
  • FIG. 13 shows an embodiment of a fuel lance 8 in the flow direction 4 and from the front.
  • This lance is designed for central fuel injection. It is dimensioned for about 10% of the total volume flow through the channel, the fuel 9 being injected transversely to the direction of flow. A longitudinal injection of the fuel in the direction of flow can of course also be provided. In this case, the injection pulse corresponds approximately to that of the main flow.
  • the injected fuel 9 is entrained by the upstream injected vortices in connection with a portion of supporting air 10 via a plurality of radial openings 17 and mixed with the main flow 4.
  • the injected fuel 9 follows the helical course of the vortices (see FIGS. 2-4) and is evenly finely distributed in the chamber downstream of the vortices.
  • FIG. 14 shows a diagram relating to the supply of fuel 9 and supporting air 10, and according to which the combustion chamber described is started up.
  • the aim here is to create those conditions when starting that guarantee an optimal mixture of the injected fuel with the main flow, i.e. optimal ignition behavior and optimal combustion in the transient range up to the full load of the combustion chamber.
  • the ordinate Y plots the amount of media injected to each other, the abscissa X the load of the system.
  • the amount of supporting air 10 is maximum at the start; it gradually decreases with increasing load of the combustion chamber, while the injected fuel 9 gradually increases. At full load, the fuel 9 still has a proportion Z of supporting air 10.

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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)
EP95810291A 1994-05-19 1995-05-03 Chambre de combustion à allumage automatique Expired - Lifetime EP0687860B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4417538A DE4417538A1 (de) 1994-05-19 1994-05-19 Brennkammer mit Selbstzündung
DE4417538 1994-05-19

Publications (3)

Publication Number Publication Date
EP0687860A2 true EP0687860A2 (fr) 1995-12-20
EP0687860A3 EP0687860A3 (fr) 1997-04-23
EP0687860B1 EP0687860B1 (fr) 2001-02-28

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Application Number Title Priority Date Filing Date
EP95810291A Expired - Lifetime EP0687860B1 (fr) 1994-05-19 1995-05-03 Chambre de combustion à allumage automatique

Country Status (5)

Country Link
US (1) US5593302A (fr)
EP (1) EP0687860B1 (fr)
JP (1) JP3631802B2 (fr)
CN (1) CN1106531C (fr)
DE (2) DE4417538A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1207350A3 (fr) * 2000-11-14 2002-07-24 ALSTOM Power N.V. Chambre de combustion et procédé de fonctionnement associé

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DE19520291A1 (de) * 1995-06-02 1996-12-05 Abb Management Ag Brennkammer
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DE19948673B4 (de) * 1999-10-08 2009-02-26 Alstom Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens
US6450108B2 (en) 2000-03-24 2002-09-17 Praxair Technology, Inc. Fuel and waste fluid combustion system
DE10128063A1 (de) * 2001-06-09 2003-01-23 Alstom Switzerland Ltd Brennersystem
DE10210034B4 (de) * 2002-03-07 2009-10-01 Webasto Ag Mobiles Heizgerät mit einer Brennstoffversorgung
DE10330023A1 (de) * 2002-07-20 2004-02-05 Alstom (Switzerland) Ltd. Wirbelgenerator mit kontrollierter Nachlaufströmung
EP1975506A1 (fr) * 2007-03-30 2008-10-01 Siemens Aktiengesellschaft Pré-chambre de combustion
EP2260238B1 (fr) * 2008-03-07 2015-12-23 Alstom Technology Ltd Procédé de fonctionnement d'un brûleur à prémélange
EP2112433A1 (fr) 2008-04-23 2009-10-28 Siemens Aktiengesellschaft Chambre de mélange
EP2116767B1 (fr) * 2008-05-09 2015-11-18 Alstom Technology Ltd Brûleur avec lance
EP2211110B1 (fr) * 2009-01-23 2019-05-01 Ansaldo Energia Switzerland AG Brûleur pour turbine à gaz
ATE554346T1 (de) * 2009-03-16 2012-05-15 Alstom Technology Ltd BRENNER FÜR EINE GASTURBINE UND VERFAHREN ZUR LOKALEN KÜHLUNG VON HEIßEN GASSTRÖMEN, DIE EINEN BRENNER DURCHLAUFEN
CN101846315B (zh) * 2009-03-24 2012-07-04 烟台龙源电力技术股份有限公司 煤粉浓缩装置和包含该煤粉浓缩装置的内燃式煤粉燃烧器
EP2261566A1 (fr) * 2009-05-28 2010-12-15 Siemens AG Brûleur et procédé de réduction d'oscillations de flammes à auto-induction dans un brûleur
EP2496883B1 (fr) 2009-11-07 2016-08-10 Alstom Technology Ltd Brûleur à prémélange pour chambre de combustion de turbine à gaz
WO2011054739A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection pour brûleur de réchauffage
WO2011054757A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection pour brûleur de réchauffage avec lances à combustible
EP2496884B1 (fr) 2009-11-07 2016-12-28 General Electric Technology GmbH Système d'injection de brûleur de postcombustion
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EP2420731B1 (fr) 2010-08-16 2014-03-05 Alstom Technology Ltd Brûleur post-combustion
US9388982B2 (en) * 2010-10-27 2016-07-12 Alstom Technology Ltd Flow deflectors for fuel nozzles
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
EP2703721B1 (fr) 2012-08-31 2019-05-22 Ansaldo Energia IP UK Limited Brûleur à prémélange
EP2775107A1 (fr) 2013-03-06 2014-09-10 Alstom Technology Ltd Procédé pour démarrer une centrale électrique à cycle combiné
EP2894405B1 (fr) * 2014-01-10 2016-11-23 General Electric Technology GmbH Dispositif à combustion séquentielle avec un gaz de dilution
EP3051206B1 (fr) * 2015-01-28 2019-10-30 Ansaldo Energia Switzerland AG Agencement de combustion séquentielle d'une turbine à gaz avec un mélangeur et un amortisseur
CN105180155A (zh) * 2015-10-23 2015-12-23 山东永能节能环保服务股份有限公司 新型高效生物质燃烧器及燃烧工艺
CN106247337A (zh) * 2016-09-28 2016-12-21 中国海洋石油总公司 一种用于天然气直接引射液态液化石油气的增热引射器
GB201806020D0 (en) * 2018-02-23 2018-05-30 Rolls Royce Conduit
CN113242761B (zh) * 2018-12-21 2023-10-27 爱尔兰国立高威大学 涡流发生器装置
CN109931628B (zh) * 2019-03-27 2020-08-04 北京理工大学 一种基于rde燃烧室的环腔旋流对喷结构
JP7257215B2 (ja) * 2019-03-27 2023-04-13 三菱重工業株式会社 音響ダンパ、燃焼器及びガスタービン

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1207350A3 (fr) * 2000-11-14 2002-07-24 ALSTOM Power N.V. Chambre de combustion et procédé de fonctionnement associé
US6688111B2 (en) 2000-11-14 2004-02-10 Alstom Technology Ltd Method for operating a combustion chamber

Also Published As

Publication number Publication date
DE4417538A1 (de) 1995-11-23
DE59509043D1 (de) 2001-04-05
CN1106531C (zh) 2003-04-23
US5593302A (en) 1997-01-14
JP3631802B2 (ja) 2005-03-23
JPH07310909A (ja) 1995-11-28
EP0687860B1 (fr) 2001-02-28
EP0687860A3 (fr) 1997-04-23
CN1117567A (zh) 1996-02-28

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