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EP1740797B1 - Turbine a gaz - Google Patents

Turbine a gaz Download PDF

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Publication number
EP1740797B1
EP1740797B1 EP05747380A EP05747380A EP1740797B1 EP 1740797 B1 EP1740797 B1 EP 1740797B1 EP 05747380 A EP05747380 A EP 05747380A EP 05747380 A EP05747380 A EP 05747380A EP 1740797 B1 EP1740797 B1 EP 1740797B1
Authority
EP
European Patent Office
Prior art keywords
cooling
shroud
region
gas turbine
blade
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
EP05747380A
Other languages
German (de)
English (en)
Other versions
EP1740797A1 (fr
Inventor
Ulrich Rathmann
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 Technology GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP05747380A priority Critical patent/EP1740797B1/fr
Publication of EP1740797A1 publication Critical patent/EP1740797A1/fr
Application granted granted Critical
Publication of EP1740797B1 publication Critical patent/EP1740797B1/fr
Anticipated expiration legal-status Critical
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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the invention relates to a blade for a gas turbine and in particular a cooling for the shroud of the blade.
  • Shrouds for gas turbine blades serve to seal and limit the leakage flow in the gap region between the blade tips and the radially opposite stator or rotor. They extend in the circumferential direction and over a certain range in the direction of the turbine axis as possible in adaptation of the contour of the inner housing or of the rotor.
  • Conventional shrouds in many cases, for the purpose of improving the seal, also include one or more sealing ribs, also referred to as cutting edges, extending from a platform of the shroud, i. a substantially flat portion of the shroud extending along the radial direction.
  • the shrouds are convectively cooled in the hot gas gas turbine, for example, in order to extend their service life EP 1013884 and EP 1083299 disclosed.
  • a bucket with a shroud is described in each case, which has a plurality of bores for a cooling air flow.
  • the holes are in communication with a cooling channel in the blade and each lead to a lateral outlet in the circumferential direction.
  • EP 1041247 discloses a gas turbine blade having inner, radially extending cooling channels which open into a plenum 42 and 44. From there extend in the plane of the shroud bores 54, 56, 58, through which the shroud is cooled by means of film cooling and convective cooling. In a variant, the bores extend obliquely from the plenum and in a slightly radial direction to the radially outer surface of the shroud platform.
  • a shroud of a gas turbine blade is thermally differently stressed along the flow direction of the hot gas as well as mechanically loaded differently in different areas. Accordingly, the requirements for cooling and mechanical strength in different areas of the shroud different. This is accommodated in the disclosed gas turbine blades by adjusting the bore diameters and other measures to vary the pressure differentials.
  • DE 103 36 863 discloses a thermal turbomachinery with blades whose shroud elements are cooled in one area by impingement cooling and in another area by convective or impingement cooling.
  • JP58047104 discloses a gas turbine with a device for cooling for blades, wherein the blade is convectively cooled by cooling air which is passed through inner channels. On the other hand, the blade is cooled by an air flow which leads through a cooling channel to the outer surface of the blade.
  • the shroud of a gas turbine blade extends circumferentially along the blade tip and in the radial direction with respect to the turbine rotor and is disposed opposite a stator housing.
  • the shroud is divided into areas which are thermally differently loaded.
  • the different areas are cooled by different cooling arrangements, each cooling arrangement allowing cooling with different physical effects adapted to the thermal load, such as film cooling, impingement cooling, convective cooling or mixed cooling.
  • the gas turbine blade has a first cooling arrangement for cooling a first region of the cover strip by cooling air from a cooling system from inside the blade.
  • This first area is the first area in the direction of the hot gas flow and therefore thermally loaded the most.
  • a second region downstream of the first region in the direction of the hot gas flow is less thermally stressed compared to the first region.
  • the second cooling arrangement that of the cooling, is arranged on a stator arranged radially opposite the gas turbine blade arranged stator, the second cooling arrangement is arranged, which serves to cool the second region of the shroud from outside the blade.
  • the first and second cooling arrangements are different from one another in that the first cooling arrangement effects a cohenive and film cooling and the second cooling arrangement effects a baffle cooling.
  • the inventive cooling of the shroud causes the thermal load of the areas appropriate cooling and a correspondingly appropriate cooling air consumption.
  • the first region of the gas turbine blade shroud in particular has an extending in the radial direction with respect to the gas turbine rotor blade extending in the longitudinal direction in the circumferential direction and in which the first cooling arrangement is arranged.
  • the blade has a plurality of bores in fluid communication with a cooling passage of the airfoil and having outlets on the hot gas side of the shroud.
  • a cooling air flow causes convective cooling of the cutting edge as it flows through the bores. After emerging from the bores, it flows along the outer surface of the shroud and effects film cooling there.
  • the stator housing which is arranged radially opposite the shroud, has a plurality of cooling channels, which are directed substantially perpendicular to the platform of the shroud. They serve to cool the second portion of the shroud in the hot gas flow direction. They are connected to the stator cooling system, which flows from this branched cooling air through the cooling channels on the platform of the shroud and there causes an impingement cooling. The cooling air then escapes in both axial directions, whereby a blocking flow in the opposite direction to the leakage flow can occur.
  • the second region of the shroud is bounded on both sides in the axial direction by radially extending cutting edges.
  • the gas turbine blade has a further third region of the cover strip in the direction of the hot gas flow, which is equipped with a third cooling arrangement.
  • This cooling arrangement has a plurality of bores which are in fluid communication with a cooling passage in the interior of the airfoil. The bores are directed at an angle to the radial in at least partially radially outward directions that direct a flow of cooling air to the radially outer portion of the shroud. Cooling air flowing through these holes causes convective cooling of this third area.
  • the holes in the plane of the shroud platform are oriented at an angle with respect to the circumferential direction so that the cooling air is blown out of the holes substantially counter to the direction of rotation of the blades.
  • the holes in the end region parallel to each other.
  • a plurality of further cooling channels are arranged, which are directed substantially perpendicular to a third region of the shroud in the direction of the hot gas flow. They serve to cool this third area.
  • the third region is delimited in the axial direction and in the opposite direction of the hot gas flow by a cutting edge.
  • the cooling channels are in fluid communication with the cooling system of the stator, whereby cooling air from the stator cooling system is directed to the end portion of the shroud and causes there a Prattkühlung.
  • the FIG. 1 shows a rotating gas turbine blade in a meridional section through the gas turbine.
  • the directions x and z indicate the axial direction, ie the direction of the machine axis, or the radial direction with respect to the gas turbine rotor. It is shown the airfoil 1 and the blade tip on which the shroud 2 is arranged. Opposite the shroud 2, in the radial outward direction with respect to the gas turbine rotor 3, the stator housing 4 is shown.
  • the gas turbine blade and the stator housing each have a cooling system 5 and 6, respectively.
  • the direction of the hot gas flow is indicated by an arrow 7. Basically, the temperature of the hot gas flow and accordingly the thermal load of the machine components along the direction 7 steadily decreases.
  • the shroud 2 is divided into three areas A, B and C.
  • the first area A is exposed to a higher temperature of the hot gas flow compared to the two subsequent areas B and C and consequently thermally loaded the most.
  • the first region has a cutting edge 8 which extends radially outwards and in the circumferential direction.
  • the cutting edge 8 has a bore 9, which is in flow communication with the cooling system 5. This bore extends, for example, circumferentially within the cutting edge. From this bore 9 branch off several further holes 10, which extend radially inwardly to an outlet on the rotor-side surface of the cutting edge, that is on the hot gas side of the shroud.
  • the branching holes 10 are in the FIG. 3 shown.
  • Cooling air from the cooling system 5 of the airfoil flows through the bore 9 and through the branching holes 10, wherein it causes a convective cooling of the cutting edge 8.
  • the outlets of the holes are each designed so that exiting cooling air flows along the surface of the blade and there causes additional film cooling.
  • the cutting edge is cooled by two different cooling mechanisms.
  • a cooling channel 11 is arranged through the wall of the housing 4, which is in communication with the cooling system in the stator housing.
  • a cooling air flow indicated by the arrow 12, flows from this cooling system through the cooling channel 11 and is preferably directed perpendicular to the shroud 2 due to its orientation.
  • the Cooling channel 11 also aligned at a different angle with respect to the shroud.
  • the cooling air flow 12 thus causes an impact cooling of the center region B of the shroud.
  • the region B is bounded in the axial direction and in the direction of the hot gas flow through the first cutting edge 8 and a second cutting edge 13.
  • the cooling air flow 12 escapes from the limited area as a leakage flow, in that the cooling air flow flows away in both axial directions via the cutting edge 8 and the cutting edge 13. In this case, depending on the operating conditions, a blocking flow against a hot gas leakage flow result.
  • a special opening or gap in the region of the second sealing blade 13 is provided, which allows a precisely controlled outflow of the cooling air.
  • a plurality of bores is arranged according to the second embodiment of the invention, which extend from the cooling system 5 of the blade and extend to the radially outer surface of the shroud. A cooling air flow through these holes cause a convective cooling of this area. they are in the FIG. 2 shown.
  • FIG. 2 shows a plan view of the inventive shroud again with the areas A, B and C. It is shown with x and y, the axial direction or the circumferential direction with respect to the turbine rotor and the outline of the blade root 14 and the dashed line the outline of the blade itself the cutting edge 8 in the region A and the cutting edge 13 in the region B are shown, which extend in the circumferential direction and serve to seal against leakage flows.
  • the region C has the holes 15 for the purpose of convective cooling of that region, wherein they extend at an angle ⁇ to the circumferential direction y.
  • the angle ⁇ is for example in a range between 2 ° and 90 °.
  • the cooling air that emerges from the holes 15 is blown in the opposite direction to the direction of rotation of the blade.
  • the holes 15 are aligned parallel to each other, so that the production is simplified.
  • FIG. 3 shows a section according to III-III in FIG. 2 and shows the cutting edge 8 in the region A of the shroud and the course of the transverse bore 9 and the bores 10 branched off from it.
  • the transverse bore 9 is connected via channel 21 in fluid communication with the cooling system of the blade.
  • the Fluid communication is ensured by an extension of the blade system cooling system; which projects into the cutting edge 8 and opens into the transverse bore 9.
  • the several branching holes 10 extend with respect to the turbine rotor substantially radially inwardly to emerge at the hot gas side of the cutting edge 8.
  • the course of the cooling flow is with arrows through the channel 21, via the transverse bore. 9 and the branching bores 10 are indicated.
  • outlets from the bore 10 are particularly permitted to effect film cooling of the hot gas side surface of the cutting edge, such as with a slightly divergent exit portion and a preferred angular range, as known in the relevant literature.
  • Preferred Methods of Preparation are the usual casting with core and drilling from the outside and then closing the hole entries by means of plugs 20, which are introduced, for example, form-fitting or materially connected (soldering, welding).
  • FIG. 4 shows the blade and a channel of the cooling system 5 in its airfoil.
  • the bore 15 extends from the channel and extends to the radially outer surface of the cover strip 2.
  • the outlet of a bore 15 is designed angled, so that the mixture with the Heisgasströmung the conditions can be advantageously influenced accordingly.
  • the angle ⁇ between the exit surface and the axis of the bore is preferably in a range between 40 ° and 140 °.
  • the angle ⁇ between the bore axis and the direction of the radial z is preferably selected in a range of 30 ° to 120 °.
  • the diameter of the bore is in a range between 0.6 and 4.5 mm, preferably in a range between 0.6 and 2.5 mm. This is to provide adequate convective cooling for this area.
  • FIG. 5 shows in a section according to IV-IV a variant of the outlet of the bores 15.
  • the exit surface is again angled and stepped with respect to the bore axis, wherein the end of the upper lip 16 is substantially perpendicular to the bore axis.
  • the dimension s is dependent on the diameter of the exit surface and is in particular in a ratio to the diameter of the bore in a range of 0.5 to 3 and also allows an advantageous influence on the mixture with the Heisgasströmung.
  • FIG. 6 shows in the same meridional section as in FIG. 1 a gas turbine blade 1 according to the third embodiment of the invention.
  • an additional channel arranged in the stator housing is directed by the cooling air from the cooling system of the housing on the shroud.
  • an impingement cooling is effected there.
  • the gas turbine blade is completely or in individual areas according to their use in the gas turbine coated with a thermal barrier coating.

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

Claims (13)

  1. Turbine à gaz comprenant un stator de turbine à gaz (4), un boîtier de stator et une aube, l'aube présentant une virole (2) qui s'étend le long de la pointe de l'aube (1) dans la direction périphérique (y) de la turbine à gaz,
    caractérisée en ce que
    l'aube (1) présente un premier agencement de refroidissement pour refroidir une première région (A) de la virole (2) par de l'air de refroidissement provenant d'un système de refroidissement (5) à l'intérieur de l'aube (1) et un deuxième agencement de refroidissement pour refroidir une deuxième région (B) de la virole (2) par de l'air de refroidissement provenant d'un système de refroidissement d'un stator (4), le deuxième agencement de refroidissement étant disposé dans le stator (4) radialement en regard de la virole (2), et le premier et le deuxième agencement de refroidissement provoquant chacun un refroidissement de type différent,
    et
    le premier agencement de refroidissement provoque un refroidissement par convection et un refroidissement par film de la première région (A) de la virole (2), et le deuxième agencement de refroidissement provoque un refroidissement par impact de la deuxième région (B) de la virole (2), et
    la première région (A) de la virole (2) est la première région dans la direction de l'écoulement de gaz chaud et cette première région présente une première ailette (8), qui s'étend dans la direction radiale par rapport à un rotor de turbine à gaz (3) et dans la direction périphérique (y), et le premier agencement de refroidissement est disposé dans la première ailette (8), la première ailette (8) présentant plusieurs alésages (9, 10) qui sont en liaison fluidique avec un système de refroidissement (5) à l'intérieur de l'aube (1),
    et le deuxième agencement de refroidissement présente un canal de refroidissement (11) à travers le boîtier de stator (4), qui est en liaison fluidique avec un système de refroidissement (6) dans le boîtier de stator (4) et qui est orienté vers la deuxième région (B) de la virole (2).
  2. Turbine à gaz selon la revendication 1,
    caractérisée en ce que
    la virole (2) présente, dans la direction de l'écoulement de gaz chaud, une deuxième ailette (13), le flux d'air de refroidissement pour le refroidissement par impact de la deuxième région (B) de la virole (2) s'échappant entre les ailettes (8, 13) et le boîtier de stator (4).
  3. Turbine à gaz selon la revendication 1,
    caractérisée en ce que
    la virole (2) présente, dans la direction de l'écoulement de gaz chaud, une deuxième ailette (13) dans laquelle est disposée une ouverture ou une fente, à travers laquelle s'échappe le flux d'air de refroidissement pour le refroidissement par impact de la deuxième région (B).
  4. Turbine à gaz selon la revendication 1,
    caractérisée en ce que
    les alésages (10) à travers l'ailette (8) présentent à chaque fois une sortie du côté gaz chaud de l'ailette (8).
  5. Turbine à gaz selon l'une quelconque des revendications 1 à 4,
    caractérisée en ce que
    la virole (2) présente une troisième région (C) avec un troisième agencement de refroidissement, le troisième agencement de refroidissement présentant plusieurs alésages (15) qui sont en liaison fluidique avec un système de refroidissement (5) à l'intérieur de l'aube (1), et qui s'étendent au moins dans une direction radiale partielle vers l'extérieur à travers la virole (2) jusqu'à la surface radialement extérieure de la virole (2).
  6. Turbine à gaz selon la revendication 5,
    caractérisée en ce que
    les alésages (15) dans la troisième région (C) présentent à chaque fois une sortie qui est orientée dans le sens opposé à la direction périphérique de la turbine à gaz.
  7. Turbine à gaz selon la revendication 5 ou 6,
    caractérisée en ce que
    les alésages (15) dans la troisième région (C) s'étendent parallèlement les uns aux autres.
  8. Turbine à gaz selon la revendication 5 ou 6,
    caractérisée en ce que
    les alésages (15) dans la troisième région (C) s'étendent suivant un angle (α) par rapport à la direction périphérique (y), lequel est compris dans une plage de 2° à 90°.
  9. Turbine à gaz selon la revendication 5 ou 6,
    caractérisée en ce que
    la surface de sortie des alésages (15) dans la troisième région (C) s'étend suivant un angle (χ) par rapport à l'axe des alésages (15), lequel est compris dans une plage de 40° à 140°.
  10. Turbine à gaz selon la revendication 5 ou 6,
    caractérisée en ce que
    l'axe des alésages (15) dans la troisième région (C) s'étend suivant un angle (β) par rapport à la direction de la radiale (z), lequel est compris dans une plage de 30° à 120°.
  11. Turbine à gaz selon la revendication 7 ou 8,
    caractérisée en ce que
    la virole (2) dans la troisième région (C) présente une lèvre (16) étagée verticalement à chaque fois par rapport à l'axe des alésages (15), et le diamètre de la surface de sortie d'un alésage (15) est à chaque fois dans un rapport de l'ordre de 0,5 à 3 par rapport au diamètre de l'alésage (15).
  12. Turbine à gaz selon la revendication 1,
    caractérisée en ce que
    la virole (2) présente une troisième région (C) avec un troisième agencement de refroidissement, le troisième agencement de refroidissement présentant plusieurs canaux de refroidissement (17) à travers le boîtier de stator (4), lesquels sont en liaison fluidique avec un système de refroidissement (6) du boîtier de stator (4) et les canaux de refroidissement (17) sont orientés vers la troisième région (C) de la virole (2).
  13. Turbine à gaz selon les revendications précédentes,
    caractérisée en ce que
    l'aube (1) est configurée au moins en partie avec une couche formant barrière thermique.
EP05747380A 2004-04-30 2005-04-19 Turbine a gaz Not-in-force EP1740797B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05747380A EP1740797B1 (fr) 2004-04-30 2005-04-19 Turbine a gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04101876A EP1591626A1 (fr) 2004-04-30 2004-04-30 Aube de turbine à gaz
PCT/EP2005/051721 WO2005106208A1 (fr) 2004-04-30 2005-04-19 Pale de turbine a gaz
EP05747380A EP1740797B1 (fr) 2004-04-30 2005-04-19 Turbine a gaz

Publications (2)

Publication Number Publication Date
EP1740797A1 EP1740797A1 (fr) 2007-01-10
EP1740797B1 true EP1740797B1 (fr) 2012-03-28

Family

ID=34929047

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04101876A Withdrawn EP1591626A1 (fr) 2004-04-30 2004-04-30 Aube de turbine à gaz
EP05747380A Not-in-force EP1740797B1 (fr) 2004-04-30 2005-04-19 Turbine a gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP04101876A Withdrawn EP1591626A1 (fr) 2004-04-30 2004-04-30 Aube de turbine à gaz

Country Status (8)

Country Link
US (1) US7273347B2 (fr)
EP (2) EP1591626A1 (fr)
KR (1) KR20070006875A (fr)
CN (1) CN1950589B (fr)
AT (1) ATE551497T1 (fr)
AU (1) AU2005238655C1 (fr)
MY (1) MY142730A (fr)
WO (1) WO2005106208A1 (fr)

Families Citing this family (33)

* Cited by examiner, † Cited by third party
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EP1591626A1 (fr) 2004-04-30 2005-11-02 Alstom Technology Ltd Aube de turbine à gaz
EP2003291B1 (fr) * 2007-06-15 2017-08-09 Ansaldo Energia Switzerland AG Aube de turbine à gaz moulée et procédé de production
EP2009248B1 (fr) * 2007-06-25 2010-05-12 Siemens Aktiengesellschaft Agencement de turbine et procédé de refroidissement d'un anneau situé au bout d'une aube de turbine
KR100857346B1 (ko) * 2007-07-06 2008-09-05 현대자동차주식회사 Ｓｏｏｔ 영향을 고려한 Ｕｒｅａ 분사 방법
US8182207B2 (en) * 2008-03-17 2012-05-22 General Electric Company Inner turbine shell support configuration and methods
CH699593A1 (de) 2008-09-25 2010-03-31 Alstom Technology Ltd Schaufel für eine gasturbine.
DE102009049649A1 (de) * 2009-10-15 2011-04-21 Abb Turbo Systems Ag Turbinenrad
US8721289B2 (en) * 2009-10-30 2014-05-13 General Electric Company Flow balancing slot
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EP1591626A1 (fr) 2005-11-02
ATE551497T1 (de) 2012-04-15
US20070071593A1 (en) 2007-03-29
CN1950589B (zh) 2012-02-22
AU2005238655C1 (en) 2011-06-09
WO2005106208A1 (fr) 2005-11-10
KR20070006875A (ko) 2007-01-11
AU2005238655A1 (en) 2005-11-10
US7273347B2 (en) 2007-09-25
MY142730A (en) 2010-12-31
CN1950589A (zh) 2007-04-18
AU2005238655B2 (en) 2010-08-26
EP1740797A1 (fr) 2007-01-10

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