EP2242915B1 - Turbine à gaz à architecture de refroidissement améliorée - Google Patents

Turbine à gaz à architecture de refroidissement améliorée Download PDF

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Publication number
EP2242915B1
EP2242915B1 EP09713405.0A EP09713405A EP2242915B1 EP 2242915 B1 EP2242915 B1 EP 2242915B1 EP 09713405 A EP09713405 A EP 09713405A EP 2242915 B1 EP2242915 B1 EP 2242915B1
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EP
European Patent Office
Prior art keywords
cooling
machine according
thermal machine
channel
flow
Prior art date
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Active
Application number
EP09713405.0A
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German (de)
English (en)
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EP2242915A1 (fr
Inventor
Hartmut Hähnle
Russell Bond Jones
Gregory Vogel
Remigi Tschuor
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General Electric Technology GmbH
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General Electric Technology GmbH
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Publication date
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Publication of EP2242915A1 publication Critical patent/EP2242915A1/fr
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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling

Definitions

  • the present invention relates to the field of thermal machines. It relates to a thermal machine according to the preamble of claim 1.
  • Gas turbines such as those offered by the applicant under, for example, the type designation GT13E2, are operated with an annular combustion chamber.
  • the combustion itself is preferably, but not exclusively premix burner (hereinafter referred to as burner), as for example from EP-A1-321809 or EP-A1-704,657
  • burner premix burner
  • Such an annular combustion chamber goes out DE-A1-196 44 378 which, in the Fig. 1 This application is reproduced in sections.
  • gas turbine 10 has a turbine housing 11, which encloses a filled with compressed combustion air plenum 14 in the combustion chamber 15.
  • the annular combustion chamber 15 Concentrically around the central rotor 12 around the plenum 14, the annular combustion chamber 15 is arranged, which merges into a hot gas duct 22.
  • the space is bounded inwardly by an inner shell 21 'and outwardly by an outer shell 21.
  • Inner shell 21 'and outer shell 21 are each divided into a parting plane in the upper part and a lower part.
  • the top and bottom of the inner and outer shell 21 ', 21 are connected in the parting plane so that an annular space is formed, which directs the hot gas generated by the burners 16 on the blades 13 of the turbine.
  • the parting line is for assembly and disassembly of the machine required.
  • the combustion chamber 15 itself is lined with special wall segments 17.
  • Inner and outer shell 21 ', 21 are convectively cooled in the embodiment described.
  • cooling air which enters the plenum 14 coming from the compressor as a compressor air flow 23, flows primarily in the opposite direction of flow of the hot gas in the hot gas duct 22 From the plenum 14 from this cooling air then flows through an outer and inner cooling channel 20 and 20 ', which cooling channels through the shells 21, 21 'are formed at a distance surrounding cooling shirts 19, 19'.
  • the cooling air flows in the cooling channels 20, 20 'along the shells 21, 21' in the direction of the combustion chamber hood surrounding the combustion chamber 15. There, the air is then available to the burners 16 as combustion air.
  • the hot gas flows to the turbine (blades 13) and thereby along the hot gas side surfaces of the inner and outer shell 21 ', 21.
  • the flow along these surfaces is not homogeneous, but is influenced by the arrangement of the burner 16th
  • Inner and outer shell 21 ', 21 are loaded both thermally and mechanically. These loads, also in connection with the mode of operation, determine the service life of the inner and outer shell 21 ', 21 and the resulting inspection intervals.
  • the above-mentioned non-uniformities of the flow occur both on the hot gas side and on the cooling air side.
  • the hot gas side nonuniformities result primarily from the burner assembly.
  • the cooling air side irregularities are primarily caused by internals in the cooling channels 20, 20 '.
  • the EP 1 482 246 A1 describes a combustion chamber with a combustion chamber side facing combustion chamber wall, are attached to the design for burner temperatures of up to 1500 ° C heat shield elements via fastening means, wherein the combustion chamber wall and the combustion chamber wall facing surface of the heat shield elements include a cooling gap, with the cooling air opposite flow direction flows to the hot gas flow within the combustion chamber.
  • flow elements narrowing the flow cross section of the cooling channel are inserted along the cooling channel on the sides of the combustion chamber wall.
  • An attachment of the flow elements along the combustion chamber wall by means of suitable form-locking connections (see column 9, lines 24 to 28).
  • the flow elements are arranged within the cooling channel such that highly thermally stressed wall sections of the heat shield element are subjected to increased cooling by increasing the cooling air flow in this area by reducing the cross section.
  • the EP 0 599 055 A1 describes a gas turbine combustion chamber with a perforated plate 3 which surrounds the combustion chamber wall at a distance, by means of which an impingement cooling air situation of the combustion chamber wall 3 is likewise created.
  • EP 1 207 273 A2 for impingement air cooling of a combustor wall 10 surrounding the hot gas passage, provides a perforated plate assembly 122 which includes a plurality of holes 26, a portion of the holes being provided with cap-like baffles capable of passing an increased portion of cooling air flow vertically through the respective holes.
  • the US 3,652,181 also describes an impingement air cooling for the combustion chamber wall surrounding the hot gas duct.
  • An embodiment of the invention is characterized in that on the outside of the shell in the cooling channel protruding internals are present, and that caused by the internals local constriction of the cooling channel is compensated by a corresponding local contouring of theméhemds.
  • the local contouring of the cooling skirt may include a dome extending in the cooling jacket over the region of the internals and projecting outwards.
  • Another embodiment of the invention provides that to compensate for a occurring at a certain place, increased thermal stress on the shell or to compensate for a caused by internals local constriction of the cooling channel at this location means for introducing additional cooling air in the Cooling channel are provided, wherein, when the cooling jacket is acted upon on the outside of under elevated pressure cooling medium, the means for introducing additional cooling air into the cooling channel preferably comprise cooling holes in the cooling jacket.
  • the thermal engine in question may be a gas turbine having a combustion chamber and the hot gas passage from the combustion chamber leading to a first series of blades.
  • the combustion chamber may be annular and separable in a parting plane, wherein the hot gas channel is bounded by an outer shell and an inner shell, and by an appropriate inner and outerdehemd an inner and outer cooling channel is formed.
  • the gas turbine comprises a compressor for compressing sucked combustion air, wherein the output of the compressor communicates with a plenum, and the combustion chamber is arranged with the adjoining hot gas channel and the adjacent cooling channels in plenum and surrounded by the plenum that compressed air from the Plenum flows against the hot gas flow in the hot gas channel through the cooling channels to burners arranged on the combustion chamber.
  • the burners may advantageously be designed as premix burners, in particular as double-cone burners.
  • the distribution of the cooling air is influenced by a (local) adaptation of the cooling channel cross-sectional profile in conjunction with existing installations in the cooling channel so that adjusts a local adjustment of the cooling air mass flow or a local adjustment of the heat transfer between shell and cooling air.
  • the cooling channel cross section is defined by the existing contour of the inner or outer shell and a modified, i. Contouring adapted to the shape of the cooling air sheets (cooling shirts), which are mounted on the inner and outer shell.
  • Fig. 2B is shown in cross-section transverse to the flow direction of the cooling air 24 and the flowing in the opposite direction of hot gas 25 between the shell 21 and the cooling jacket 19 formed cooling channel having a constant in the illustrated section flow cross-section.
  • a local change of the flow cross section can now be brought about by providing the cooling jacket (locally) with a bulge in the form of a dome 26.
  • the dome 26 which can extend in the flow direction (perpendicular to the plane) over a greater length (see Fig. 3B and 3D ), results in a local enlargement of the cooling channel cross-section, which leads to a locally improved cooling and thus can contribute to the reduction of an occurring at this point increased thermal load.
  • Such a step is particularly suitable when in the cooling channel 20 as obstacles inwardly projecting ribs 27 on the outside of the shell 21 are present.
  • Such a local dome 26 lends itself to the local improvement of the cooling, in particular, if - as in FIGS. 3A and 3B shown - special, the cooling flow obstructing internals 28 in the cooling channel 20 are present.
  • the dome 26 is then conveniently adapted in width and length to the disabling internals 28.
  • cooling channel 20 In addition or as an alternative to the dome-like local extension (26) of the cooling channel 20 but can also according to 3C and 3D additional cooling air 29 are guided through corresponding openings in the cooling jacket 19 to the critical point. For this purpose, it is necessary that on the outside of thedehemdes cooling air under higher pressure, in particular from the surrounding plenum 14, is available.
  • FIG. 4 to 6 is shown in a perspective side view (divisible in a dividing plane 31, outer)dehemd 19 for a gas turbine annular combustion chamber with local adjustments according to another embodiment of the invention.
  • the cooling jacket 19 is composed of a plurality of similar segments 30.
  • a selected segment 32 is provided, which has local modifications to optimize the cooling.
  • this selected segment 32 which adjoins the parting plane 31 and includes a corresponding terminal strip 33, on the one hand equipped with an elongated dome 26.
  • cooling openings 35 and 34 are arranged in the segment sheet, by - analogous to 3C and 3D - Additional cooling air can enter from outside into the cooling channel.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (14)

  1. Machine thermique comportant
    un canal (22) à gaz chaud délimité à l'extérieur par une coquille (21, 21'),
    un canal de refroidissement (20, 20') formé par la coquille (21, 21'),
    une chemise de refroidissement (19, 19') qui entoure l'extérieur de la coquille (21, 21') étant formée sur le côté extérieur de la coquille (21, 21'), caractérisée en ce que
    pour compenser des irrégularités locales de la sollicitation thermique de la coquille (21, 21') ou de l'écoulement du fluide de refroidissement dans le canal de refroidissement (20, 20'), la chemise de refroidissement (19, 19') présente un bombement local en forme de dôme qui entraîne une augmentation locale de la section transversale du canal de refroidissement.
  2. Machine thermique selon la revendication 1, caractérisée en ce que des garnitures (28) qui pénètrent dans le canal de refroidissement (20, 20') sont prévues sur le côté extérieur de la coquille (21, 21') et en ce que le rétrécissement du canal de refroidissement (20, 20') provoqué par les garnitures (28) est compensé par un contour local correspondant de la chemise de refroidissement (19, 19').
  3. Machine thermique selon la revendication 2, caractérisée en ce que le contour local de la chemise de refroidissement (19, 19') comporte le dôme (26) de la chemise de refroidissement (19, 19'), bombé vers l'extérieur et s'étendant au-dessus de la zone occupée par les garnitures (28).
  4. Machine thermique selon les revendications 1 ou 2, caractérisée en ce que pour compenser une sollicitation thermique plus forte en un emplacement défini de la coquille (21, 21') ou pour compenser un rétrécissement local du canal de refroidissement (20, 20') provoqué par les garnitures (28), des moyens (34, 35) permettant d'introduire de l'air supplémentaire de refroidissement (29) dans le canal de refroidissement (20, 20') sont prévus en cet endroit.
  5. Machine thermique selon la revendication 4, caractérisée en ce que la chemise de refroidissement (19, 19') est alimentée sur le côté extérieur par un fluide de refroidissement mis sous pression et en ce que les moyens d'introduction d'air supplémentaire de refroidissement (29) dans le canal de refroidissement (20, 20') comportent des ouvertures de refroidissement (34, 35) ménagées dans la chemise de refroidissement (19, 19').
  6. Machine thermique selon l'une des revendications 1 à 5, caractérisée en ce que la machine thermique est une turbine à gaz (10) dotée d'une chambre de combustion (15) et en ce que le canal (22) à gaz chaud conduit de la chambre de combustion (15) à une première série d'aubes mobiles (13).
  7. Machine thermique selon la revendication 6, caractérisée en ce que la chambre de combustion (15) a une forme annulaire et peut être séparée dans un plan de séparation (31), en ce que le canal (22) à gaz chaud est délimité par une coquille extérieure (21) et une coquille intérieure (21') et en ce qu'un canal intérieur et un canal extérieur de refroidissement (20 et 20') sont formés par une chemise de refroidissement intérieure et une chemise de refroidissement extérieure (19 et 19').
  8. Machine thermique selon la revendication 7, caractérisée en ce que la turbine à gaz (10) comporte un compresseur qui comprime l'air de combustion aspiré, en ce que la sortie du compresseur est reliée à un collecteur (14) et en ce que la chambre de combustion (15) est disposée dans le collecteur (14) et entourée par le collecteur (14) avec le canal (22) à gaz chaud qui s'y raccorde et les canaux de refroidissement (20, 20') adjacents, en ce que l'air comprimé provenant du collecteur (14) s'écoule en opposition à l'écoulement de gaz chaud dans le canal (22) à gaz chaud par les canaux de refroidissement (20, 20') pour aboutir à des brûleurs (16) disposés dans la chambre de combustion (15) .
  9. Machine thermique selon l'une des revendications 1 à 8, caractérisée en ce que les brûleurs (16) sont configurés comme brûleurs à pré-mélange.
  10. Machine thermique selon la revendication 9, caractérisée en ce que le brûleur (16) à pré-mélange est constitué d'au moins deux parties coniques de coquille creuses, emboîtées l'une dans l'autre dans la direction d'écoulement, pour former un corps, en ce que la section transversale de l'espace intérieur formé par les parties coniques de coquille creuses augmente dans la direction d'écoulement, en ce que les axes de symétrie longitudinaux de ces parties coniques de coquille sont mutuellement décalés de telle sorte que les parois voisines des parties coniques de coquille forment dans leur extension longitudinale des fentes tangentielles ou des canaux qui permettent l'introduction d'un écoulement d'air de combustion dans l'espace intérieur formé par les parties coniques de coquille.
  11. Machine thermique selon la revendication 9, caractérisée en ce que le brûleur (16) à pré-mélange est constitué d'au moins deux parties coniques de coquille creuses, emboîtées l'une dans l'autre dans la direction d'écoulement pour former un corps, en ce que la section transversale de l'espace intérieur formé par les parties creuses de coquille s'étend en cylindre ou quasi en cylindre dans la direction d'écoulement, en ce que les axes de symétrie longitudinaux de ces parties de coquille sont mutuellement décalés de telle sorte que les parois voisines des parties de coquille forment dans leur extension longitudinale des fentes tangentielles ou des canaux qui permettent l'introduction d'un écoulement d'air de combustion dans l'espace intérieur formé par les parties de coquille et en ce que l'espace intérieur présente un corps intérieur dans la section transversale diminue dans la direction d'écoulement.
  12. Machine thermique selon la revendication 11, caractérisée en ce que le corps intérieur se rétrécit en forme de cône ou quasi en forme de cône dans la direction d'écoulement.
  13. Machine thermique selon l'une des revendications 10 à 12, caractérisée en ce que dans une zone de transition entre un tourbillonneur qui fait partie du brûleur (16) à pré-mélange et un tube de mélange raccordé en aval, des canaux de transition qui transfèrent l'écoulement formé dans le tourbillonneur en la section transversale d'écoulement du tube de mélange située en aval des canaux de transition présente.
  14. Machine thermique selon l'une des revendications 10 à 13, caractérisée en ce que le nombre des canaux de transition correspond à celui des parties coniques de coquille ou des parties de coquille.
EP09713405.0A 2008-02-20 2009-02-16 Turbine à gaz à architecture de refroidissement améliorée Active EP2242915B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2442008 2008-02-20
PCT/EP2009/051763 WO2009103671A1 (fr) 2008-02-20 2009-02-16 Turbine à gaz à architecture de refroidissement améliorée

Publications (2)

Publication Number Publication Date
EP2242915A1 EP2242915A1 (fr) 2010-10-27
EP2242915B1 true EP2242915B1 (fr) 2018-06-13

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Family Applications (1)

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EP09713405.0A Active EP2242915B1 (fr) 2008-02-20 2009-02-16 Turbine à gaz à architecture de refroidissement améliorée

Country Status (5)

Country Link
US (1) US8413449B2 (fr)
EP (1) EP2242915B1 (fr)
AU (1) AU2009216788B2 (fr)
MY (1) MY154620A (fr)
WO (1) WO2009103671A1 (fr)

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WO2017058155A1 (fr) * 2015-09-29 2017-04-06 Siemens Aktiengesellschaft Arrangement de refroidissement par contact pour conduites de transition de turbine à gaz
US10228135B2 (en) * 2016-03-15 2019-03-12 General Electric Company Combustion liner cooling
US10598380B2 (en) * 2017-09-21 2020-03-24 General Electric Company Canted combustor for gas turbine engine
US10697634B2 (en) 2018-03-07 2020-06-30 General Electric Company Inner cooling shroud for transition zone of annular combustor liner

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Also Published As

Publication number Publication date
US20110110761A1 (en) 2011-05-12
WO2009103671A1 (fr) 2009-08-27
MY154620A (en) 2015-07-15
AU2009216788A1 (en) 2009-08-27
AU2009216788B2 (en) 2014-09-25
US8413449B2 (en) 2013-04-09
EP2242915A1 (fr) 2010-10-27

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