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EP2179143B1 - Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz - Google Patents

Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz Download PDF

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Publication number
EP2179143B1
EP2179143B1 EP08786927A EP08786927A EP2179143B1 EP 2179143 B1 EP2179143 B1 EP 2179143B1 EP 08786927 A EP08786927 A EP 08786927A EP 08786927 A EP08786927 A EP 08786927A EP 2179143 B1 EP2179143 B1 EP 2179143B1
Authority
EP
European Patent Office
Prior art keywords
wall
gap
turbine
circumferential direction
negative
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.)
Not-in-force
Application number
EP08786927A
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German (de)
English (en)
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EP2179143A2 (fr
Inventor
Ulrich Steiger
Willy Heinz Hofmann
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.)
GE Vernova GmbH
Original Assignee
Alstom Technology AG
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Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2179143A2 publication Critical patent/EP2179143A2/fr
Application granted granted Critical
Publication of EP2179143B1 publication Critical patent/EP2179143B1/fr
Not-in-force legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor

Definitions

  • the present invention relates to a gas turbine plant, in particular for a power plant, according to the preamble of claim 1.
  • Such a gas turbine plant usually comprises a combustion chamber which radially delimits a combustion gas path at least in an annular outlet region with a chamber inner wall and with a chamber outer wall. Furthermore, such a gas turbine plant usually comprises a turbine which radially delimits a turbine gas path at least in a stationary annular inlet area with a turbine inner wall and with a turbine outer wall.
  • the gas turbine plant may also be equipped with a radially inwardly and / or radially outwardly axially extending gap between the combustion chamber and the turbine, at which the inner and / or outer chamber wall and the inner and / or or outer turbine wall ends.
  • a cooling gas supply can expediently also be provided, which introduces a cooling gas into the turbine gas path and / or into the combustion gas path via the gap.
  • the EP 1 741 877 A1 shows a gas turbine plant with the features of the preamble of claim 1. This is to ensure a dew point-free guide surface for the gas flow in the transition region between the combustion chamber and turbine, which may be provided instead of the negative stages that the upstream guide surface part at least with the surface of the downstream adjoining Guide surface part is aligned. Moreover, in the EP 1 741 877 A1 addressed the possibility of forming or arranging the guide surface parts delimiting the gap so that the cooling air gap almost completely closes during operation and ideally forms a "zero gap", cf. the section [0041] of EP 1 741 877 A1 ,
  • the wall surface part arranged upstream of the gap can be provided on its side facing away from the gas flow with grooves which form sufficient openings for the cooling air.
  • the EP 1 674 659 A2 shows another gas turbine plant; a gap cooling is not addressed. Due to tolerance accumulations in the Production or the installation of the guide surface for the hot gas forming platform parts may different radial heights of the individual platform surfaces and the platform leading edges occur, which may occur in addition to negative stages and positive stages in which the respective downstream platform surface opposite the respective upstream platform surface in the Projecting gas path projecting radially. Nevertheless, in order to be able to ensure an undisturbed flow on the wall surfaces as far as possible, the platform edges on the steps are rounded with a comparatively large radius, cf. the section [0069] of EP 1 674 659 A2 ,
  • the EP 1 731 711 A1 shows a further possibility of the design of the transition between the combustion chamber and turbine unit of a gas turbine plant.
  • it is envisaged to avoid penetration of hot gas in gaps between successive in the flow direction of the hot gas platform parts, which form a hot gas flow leading wall.
  • it is intended to form the upstream transverse edge of each platform with a curved course.
  • EP 0 902 164 A1 is provided in a gas turbine plant with a cooling gas supply via a gap between the turbine wall and the combustion chamber wall, the gap-side openings of cooling air ducts to be arranged or aligned so that the turbine-side edge surface of the gap is acted upon substantially tangentially with cooling air.
  • a gas turbine is known in which a row of guide vanes has on its inflow side a plurality of radially in the gas path projecting flow guide. With the aid of these flow guide elements, a leakage flow flowing around the blade tips from upstream rotor blades can be reduced or deflected in the axial direction so as to increase the efficiency of the gas turbine.
  • the invention deals with the problem of providing for a gas turbine plant of the type mentioned in an improved embodiment, which is characterized in particular by an increased efficiency.
  • the invention is based on the general idea of achieving a pressure distribution in the gap influencing the flow of cooling gas by a specific positioning of circumferentially alternating positive and negative steps along the gap.
  • This pressure distribution can be specifically set up so that areas with increased cooling demand are subjected to a higher cooling gas flow than areas with a smaller cooling demand. As a result, the total amount of cooling gas required can be reduced, which ultimately increases the efficiency of the gas turbine plant.
  • the combustion chamber wall or the turbine wall is correspondingly contoured in the end section adjoining the gap.
  • the circumferentially varying contours of the respective chamber wall and the respective turbine wall in the region of the radially inner gap and / or in the region of the radially outer gap can be selected and designed on the basis of different criteria.
  • a distribution of alternating pressure sides and suction sides of guide vanes of a stator blade row arranged in the stationary inlet region in the circumferential direction can be used.
  • This guide blade row arranged in the entry region is usually the so-called "first guide blade row”.
  • the pressure sides and suction sides of the vanes cause Also upstream to the gap varying pressures in the circumferential direction, which may affect the flow of cooling gas in the gap.
  • a pressure distribution which varies in the circumferential direction during operation of the gas turbine plant at or in the exit region of the combustion chamber can also be taken into account. It has been shown that different flow velocities or varying pressures can occur in the outlet area of the combustion chamber in the circumferential direction.
  • the pressure distribution or velocity distribution which arises during steady-state operation of the gas turbine can be stationary and could, for example, be due to the burner arranged distributed in the circumferential direction in a multi-burner combustion chamber.
  • the pressures varying in the circumferential direction in the exit region of the combustion chamber also influence the flow of cooling gas through the gap. By appropriate consideration of the pressure distribution in the outlet region of the combustion chamber, the disadvantageous influence on the cooling gas flow can be reduced.
  • FIG. 1 shows a highly simplified axial section of a gas turbine plant in the region of a gap between a combustion chamber and a turbine.
  • FIG. 1 includes a gas turbine plant 1, which is preferably used in a power plant, ie stationary, a combustion chamber 2 and a turbine 3, between which an axial gap 4 is arranged. Furthermore, a cooling gas supply 5 indicated by arrows is provided. As reference for the radial and axial orientation is in Fig. 1 a longitudinal center axis or axis of rotation X entered.
  • the combustion chamber 2 has, at least in an annular outlet region 6, a chamber inner wall 7 and a chamber outer wall 8, which together radially bound a combustion chamber gas path 9 indicated by an arrow.
  • the turbine 3 has, at least in a stationary, ie stator, annular inlet region 10, a turbine inner wall 11 and a turbine outer wall 12, which together define a radially indicated by an arrow turbine gas path 13.
  • the turbine 3 in the stationary inlet region 10 can usually have a row of guide vanes 14 with a plurality of guide vanes 15 which are adjacent in the circumferential direction. Since this vane row 14 is the first row of blades impinged by the hot gases of the combustion chamber 2, it is usually also referred to as the first row of stator blades 14.
  • the gap 4 consists in the example shown of a radially inner gap 16 and a radially outer gap 17.
  • the radially inner gap 16 is referred to below as the inner gap 16 or inner gap 16.
  • the radially outer gap 17 is also referred to as the outer gap 17 or outer gap 17.
  • the chamber inner wall 7 and the turbine inner wall 11 each end axially.
  • the chamber outer wall 8 and the turbine outer wall 12 each end axially.
  • the cooling gas feed 5 is designed such that it introduces a cooling gas into the turbine gas path 13 or into the combustion gas path 9 via the gap 4 or via the respective sub-gap 16 or 17.
  • the introduction of cooling gas into the gap 4 serves to avoid the entry of hot gases from the combustion gas path 9 or from the turbine gas path 13 through the gap 4 in the areas behind the respective chamber walls 7, 8 and turbine walls 11, 12th
  • the turbine walls 7, 8 may be formed, for example, by heat shield elements or by so-called liners 18.
  • the turbine walls 11, 12 can by platforms 19 and 20, which are formed on the respective blade root radially outside and inside, be formed.
  • alternating positive and negative steps are formed in the axial direction. If we achieve this by means of a corresponding shaping of an end section of the respective turbine wall 11, 12 or of the respective chamber wall 7, 8 adjoining the respective gap 4 or 16 or 17.
  • An end section of the chamber inner wall 7 is designated 21, an end section of the chamber outer wall 8 is denoted by 22, an end portion of the turbine inner wall 11 is denoted by 23 and an end portion of the turbine outer wall 12 is denoted by 24.
  • Regions of the end portions 21 to 24 lying in the sectional plane are shown by solid lines, while offset portions of the end portions 21 to 24 thereof are shown by broken lines.
  • the named stages are denoted by the lowercase letters a to d.
  • a denotes a positive step formed on the inner gap 16
  • b denotes a negative step formed on the inner gap 16.
  • a positive stage at the outer gap 17 is denoted by c
  • d denotes a negative step at the outer gap 17.
  • a positive stage a, c is present when the respective downstream wall 11, 12 protrudes radially into the respective gas path 9, 13 with respect to the respective upstream wall 7, 8.
  • there is a negative stage b, d when the respective upstream wall 7, 8 projecting radially projecting into the respective gas path 9, 13 with respect to the respective downstream wall 11, 12.
  • the positive stage a can be realized, for example, that the combustion chamber inner wall 7 in the adjacent to the gap 4 and the inner gap 16 end portion 21 in the positive stage a relative to the in the circumferential direction on both sides of the positive Stage a adjacent areas radially offset inwardly.
  • the inner positive stage a can thus be e.g. be realized only by contouring the chamber inner wall 7 in the end portion 21.
  • the inner positive stage a can be realized by the fact that the turbine inner wall 11 in the associated end section 23 is offset radially outward in the region of the positive step a relative to the regions adjoining the positive step a in the circumferential direction. In this way, the positive stage a can be realized in principle only by a corresponding contouring of the turbine inner wall 11 in the end portion 23.
  • This negative step b can be realized in that the burner inner wall 7 in which the inner gap 16 adjacent end portion in the region of the negative stage b relative to the circumferentially on both sides of the negative step b adjacent areas radially offset outwardly extends.
  • the negative step b can also be realized in that the turbine inner wall 11 is offset radially inwardly in the region adjacent to the inner gap 16 in the region of negative steps b relative to the areas adjacent to the negative step b in the circumferential direction.
  • the negative stage b can be realized by a combination of the above measures.
  • the positive stage c at the outer gap 17 can be realized in that the turbine outer wall 12 in the adjoining the outer gap 17 end portion 24 in the positive stage c relative to the circumferentially on both sides of the positive stage c adjacent areas radially inwardly offset runs.
  • the negative step d be realized, for example, that the combustion chamber outer wall 8 in the adjacent to the outer gap 17 end portion 22 in the negative stage d relative to the circumferentially on both sides of the negative step d adjacent areas radially inwardly staggered.
  • the negative stage d at the outer gap 17 can be realized in that the turbine outer wall 12 in the adjoining the outer gap 17 end portion 24 in the negative stage d relative to the circumferentially on both sides of the negative step d adjacent areas offset radially outwards. It is clear that a combination of the two above measures is also preferably realized in order to form the respective negative step d at the outer gap 17.
  • the alternately arranged in the circumferential direction arrangement of positive and negative stages a, b, c, d depending on a cooling demand is formed, which adjusts the operation of the gas turbine plant 1 at the respective gap 4 or at the inner gap 16 and / or on the outer gap 17 and in the circumferential direction varies.
  • this cooling demand curve is present in the gap 16, 17 at a stationary operating state of the gas turbine plant 1 is substantially stationary.
  • a negative step b, d can be provided in this area.
  • setting pressure conditions can be targeted realize a pressure drop and thus an acceleration or a higher flow rate for the cooling gas.
  • a positive step a, c can be realized, which leads to an increase in pressure and thus to a deceleration or to a reduced flow velocity in the cooling gas.
  • a distribution in the circumferential direction of pressure sides and suction sides of the guide vanes 15 of the first row of guide vanes 14 can be taken into account.
  • These pressure sides and suction sides alternate in the circumferential direction and result from the profiling of the guide vanes 15.
  • alternating pressure sides and suction sides influence the pressure in the respective gas path 9, 13 also in the counterflow direction and at least up to the gap 4 a corresponding consideration of this distribution of the pressure sides and suction sides in the design of the steps at the gap 4, their influence can be reduced accordingly or used to set the desired cooling gas distribution.
  • flow conditions may arise in its gas path 9, which generate flow velocities or varying pressures varying at least in the outlet region 6 in the circumferential direction.
  • this pressure distribution varying in the circumferential direction can be stationary in a stationary operating state of the gas turbine plant 1. Accordingly, here too, the influence of a pressure distribution generated in the gap 4 by the operation of the combustion chamber 2 can be reduced or utilized for the desired cooling gas distribution by suitable design of stages a to d.
  • the measures proposed according to the invention are characterized by the fact that a significant influence of the cooling gas flow in the gap 4 can be realized without appreciably increasing the surface of the combustion chamber 2 or the turbine 3 exposed to the hot working gases becomes.
  • An enlarged surface as it is realized for example by projecting into the gas path Strömungsleitieri simultaneously increases the cooling demand for the flow guide and is disadvantageous in this respect.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Installation de turbine à gaz, en particulier pour une centrale génératrice d'énergie, comprenant
    - une chambre de combustion (2), qui délimite radialement un chemin de gaz de chambre de combustion (9) au moins dans une région de sortie annulaire (6) avec une paroi interne de chambre (7) et une paroi externe de chambre (8),
    - une turbine (3) qui délimite radialement un chemin de gaz de turbine (13) au moins dans une région d'entrée stationnaire annulaire (10) avec une paroi interne de turbine (11) et une paroi externe de turbine (12),
    - une fente (4 ; 16, 17) prévue radialement à l'intérieur et/ou radialement à l'extérieur axialement entre la chambre de combustion (2) et la turbine (3), au niveau de laquelle se terminent la paroi interne de chambre et/ou la paroi externe de chambre (7, 8) et la paroi interne de turbine et/ou la paroi externe de turbine (11, 12),
    - un apport en gaz de refroidissement (5), qui introduit par le biais de la fente (4 ; 16, 17) un gaz de refroidissement dans le chemin de gaz de turbine (13) et/ou dans le chemin de gaz de chambre de combustion (9),
    - une portion d'extrémité (21, 22, 23, 24) de la paroi de turbine respective (11, 12) et/ou de la paroi de chambre respective (7, 8), adjacente à la fente (4 ; 16, 17) étant formée radialement à l'intérieur et/ou radialement à l'extérieur de telle sorte que des étages négatifs (b, d) soient formés au niveau de la fente (4 ; 16, 17), au niveau desquels la paroi respective située en amont (7, 8) fait saillie radialement vers l'intérieur par rapport à la paroi respective située en aval (11, 12), dans le chemin de gaz respectif (9, 13),
    caractérisée en ce que
    les étages négatifs (b, d) alternent au niveau de la fente (4 ; 16, 17) dans la direction périphérique avec des étages positifs (a, c), au niveau desquels la paroi respective située en aval (11, 12) fait saillie radialement vers l'intérieur par rapport à la paroi respective située en amont (7, 8) dans le chemin de gaz respectif (9, 13), l'agencement alterné dans la direction périphérique des étages (a, b, c, d) positifs et négatifs étant sélectionné en fonction d'un besoin de refroidissement s'établissant pendant le fonctionnement de l'installation de turbine à gaz (1) au niveau de la fente (4 ; 16, 17) et variant dans la direction périphérique.
  2. Installation de turbine à gaz selon la revendication 1,
    caractérisée en ce que
    l'agencement alterné dans la direction périphérique des étages (a, b, c, d) positifs et négatifs est sélectionné en fonction d'une répartition dans la direction périphérique d'une alternance de côtés de pression et de côtés d'aspiration d'aubes directrices (15) d'une (première) rangée d'aubes directrices (14) disposée dans une région d'entrée stationnaire (10).
  3. Installation de turbine à gaz selon l'une quelconque des revendications 1 et 2,
    caractérisée en ce que
    l'agencement alterné dans la direction périphérique des étages (a, b, c, d) positifs et négatifs est sélectionné en fonction de vagues d'étrave d'aubes directrices (15) se produisant pendant le fonctionnement de l'installation de turbine à gaz (1), se suivant à distance les unes des autres dans la direction périphérique, et se propageant vers l'amont, d'une (première) rangée d'aubes directrices (14) disposée dans une région d'entrée stationnaire (10).
  4. Installation de turbine à gaz selon l'une quelconque des revendications 1 à 3,
    caractérisée en ce que
    l'agencement alterné dans la direction périphérique des étages (a, b, c, d) positifs et négatifs est sélectionné en fonction d'une répartition de pression s'établissant pendant le fonctionnement de l'installation de turbine à gaz (1) au niveau de ou dans la région de sortie (6) de la chambre de combustion (2), et variant dans la direction périphérique.
  5. Installation de turbine à gaz selon l'une quelconque des revendications 1 à 4,
    caractérisée en ce que
    sur la fente (4 ; 16) est formé radialement à l'intérieur un étage positif (a), par le fait que la paroi interne de chambre de combustion (7) s'étend de manière décalée radialement vers l'extérieur dans la portion d'extrémité (21) adjacente à la fente (4 ; 16) dans la région de l'étage positif (a) par rapport aux régions adjacentes dans la direction périphérique de chaque côté de l'étage positif (a) et/ou par le fait que la paroi interne de turbine (11) s'étend de manière décalée radialement vers l'extérieur dans la portion d'extrémité (23) adjacente à la fente (4 ; 16) dans la région de l'étage positif (a) par rapport aux régions adjacentes dans la direction périphérique de chaque côté de l'étage positif (a).
  6. Installation de turbine à gaz selon l'une quelconque des revendications 1 à 5,
    caractérisée en ce que
    sur la fente (4 ; 16) est formé radialement à l'intérieur un étage négatif (b), par le fait que la paroi interne de chambre de combustion (7) s'étend de manière décalée radialement vers l'extérieur dans la portion d'extrémité (6) adjacente à la fente (4 ; 16) dans la région de l'étage négatif (b) par rapport aux régions adjacentes dans la direction périphérique de chaque côté de l'étage négatif (b) et/ou par le fait que la paroi interne de turbine (11) s'étend de manière décalée radialement vers l'intérieur dans la portion d'extrémité (23) adjacente à la fente (4 ; 16) dans la région de l'étage négatif (b) par rapport aux régions adjacentes dans la direction périphérique de chaque côté de l'étage négatif (b).
  7. Installation de turbine à gaz selon l'une quelconque des revendications 1 à 6,
    caractérisée en ce que
    sur la fente (4 ; 17) est formé radialement à l'extérieur un étage positif (c), par le fait que la paroi externe de chambre de combustion (8) s'étend de manière décalée radialement vers l'extérieur dans la portion d'extrémité (22) adjacente à la fente (4 ; 17) dans la région de l'étage positif (c) par rapport aux régions adjacentes dans la direction périphérique de chaque côté de l'étage positif (c) et/ou par le fait que la paroi externe de turbine (12) s'étend de manière décalée radialement vers l'intérieur dans la portion d'extrémité (24) adjacente à la fente (4 ; 17) dans la région de l'étage positif (c) par rapport aux régions adjacentes dans la direction périphérique de chaque côté de l'étage positif (c).
  8. Installation de turbine à gaz selon l'une quelconque des revendications 1 à 7,
    caractérisée en ce que
    sur la fente (4 ; 17) est formé radialement à l'extérieur un étage négatif (d), par le fait que la paroi externe de chambre de combustion (8) s'étend de manière décalée radialement vers l'intérieur dans la portion d'extrémité (22) adjacente à la fente (4 ; 17) dans la région de l'étage négatif (d) par rapport aux régions adjacentes dans la direction périphérique de chaque côté de l'étage négatif (d) et/ou par le fait que la paroi externe de turbine (12) s'étend de manière décalée radialement vers l'extérieur dans la portion d'extrémité (24) adjacente à la fente (4 ; 17) dans la région de l'étage négatif (d) par rapport aux régions adjacentes dans la direction périphérique de chaque côté de l'étage négatif (d).
  9. Installation de turbine à gaz selon l'une quelconque des revendications 1 à 8,
    caractérisée en ce que
    dans la direction périphérique, toutes les transitions entre des régions associées à différents étages (a, b, c, d) dans chaque portion d'extrémité (21, 22, 23, 24) de la paroi interne de chambre de combustion (7) et/ou de la paroi externe de chambre de combustion (8) et/ou de la paroi interne de turbine (11) et/ou de la paroi externe de turbine (12) sont configurées de manière continue.
EP08786927A 2007-08-06 2008-08-06 Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz Not-in-force EP2179143B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007037070 2007-08-06
PCT/EP2008/060320 WO2009019282A2 (fr) 2007-08-06 2008-08-06 Installation de turbine à gaz

Publications (2)

Publication Number Publication Date
EP2179143A2 EP2179143A2 (fr) 2010-04-28
EP2179143B1 true EP2179143B1 (fr) 2011-01-26

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EP08786927A Not-in-force EP2179143B1 (fr) 2007-08-06 2008-08-06 Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz

Country Status (5)

Country Link
US (1) US8132417B2 (fr)
EP (1) EP2179143B1 (fr)
AT (1) ATE497087T1 (fr)
DE (1) DE502008002497D1 (fr)
WO (1) WO2009019282A2 (fr)

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US7195454B2 (en) 2004-12-02 2007-03-27 General Electric Company Bullnose step turbine nozzle
EP1731711A1 (fr) 2005-06-10 2006-12-13 Siemens Aktiengesellschaft Transition de la chambre de combustion à la turbine, écran thermique et aube du distributeur de turbine
EP1741877A1 (fr) 2005-07-04 2007-01-10 Siemens Aktiengesellschaft Écran thermique et aube de distributeur pour une turbine à gaz
ATE497087T1 (de) 2007-08-06 2011-02-15 Alstom Technology Ltd Spaltkühlung zwischen brennkammerwand und turbinenwand einer gasturbinenanlage

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2428647A1 (fr) * 2010-09-08 2012-03-14 Alstom Technology Ltd Zone de dépassement pour une chambre de combustion d'une turbine à gaz
DE102014221783A1 (de) * 2014-10-27 2016-04-28 Siemens Aktiengesellschaft Heißgaskanal

Also Published As

Publication number Publication date
WO2009019282A2 (fr) 2009-02-12
EP2179143A2 (fr) 2010-04-28
US8132417B2 (en) 2012-03-13
US20100146988A1 (en) 2010-06-17
DE502008002497D1 (de) 2011-03-10
WO2009019282A3 (fr) 2009-05-07
ATE497087T1 (de) 2011-02-15

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