EP1766192B1 - Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant - Google Patents

Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant Download PDF

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Publication number
EP1766192B1
EP1766192B1 EP05766734A EP05766734A EP1766192B1 EP 1766192 B1 EP1766192 B1 EP 1766192B1 EP 05766734 A EP05766734 A EP 05766734A EP 05766734 A EP05766734 A EP 05766734A EP 1766192 B1 EP1766192 B1 EP 1766192B1
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EP
European Patent Office
Prior art keywords
vane
turbulators
platform
blade
cooling channel
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.)
Active
Application number
EP05766734A
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German (de)
English (en)
Other versions
EP1766192A1 (fr
Inventor
Hans-Thomas Bolms
Andreas Heselhaus
Roland Häbel
Torsten Koch
Ralf Müsgen
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.)
Siemens AG
Original Assignee
Siemens 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
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Priority to EP05766734A priority Critical patent/EP1766192B1/fr
Priority to PL05766734T priority patent/PL1766192T3/pl
Publication of EP1766192A1 publication Critical patent/EP1766192A1/fr
Application granted granted Critical
Publication of EP1766192B1 publication Critical patent/EP1766192B1/fr
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Anticipated expiration legal-status Critical

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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/12—Manufacture by removing material by spark erosion methods
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/291—Three-dimensional machined; miscellaneous hollowed
    • 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
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a blade wheel of a turbine with a blade whose blade root is supported on a wheel disc, and in which there is at least one cooling channel between the wheel disc of the turbine and the blade root. Furthermore, the invention relates to a blade of such a paddle wheel.
  • Paddle wheels of the type mentioned are used, for example, in stationary gas turbines as blade wheels, which are arranged in the flow direction of fuel gas behind a combustion chamber of the gas turbine and exposed there to high temperatures.
  • the cooling of the blades and in particular the blade roots of such high-temperature loaded gas turbine blades is particularly complicated due to the required complex cooling fluid management and difficult seals at the same time high centrifugal force.
  • convective cooling and other measures are currently being used to enhance the heat transfer between a cooling fluid flowing through cooling channels on the blade root and the blade root. Often, only a comparatively small amount of cooling fluid is available, so that only a small heat flow can be dissipated through a platform of the blade root. Thus, the platform surface temperature can only be lowered slightly.
  • the platform extends from an upstream edge to a downstream edge with respect to the hot gas flowing through the gas turbine in the axial direction.
  • the platform has a downstream, in Circumferential direction of the turbine disk extending downstream edge, which projects beyond the axial width of the turbine disk in the manner of a eaves addition.
  • the cooling air flow influencing structural elements are provided at the bottom of the downstream edge of the platform several. Guide vanes that rapidly rotate with the rotor move over the more or less stationary cooling air and cause a flow deflection of the cooling air from the circumferential direction in the axial direction.
  • both a turbulator-like local base panel and axially extending ribs are provided at the bottom of the platform.
  • the base panel and the ribs locally increase the heat transfer from the downstream edge of the platform into the cooling air bypassing on the underside.
  • the invention has for its object to provide a paddle wheel according to claim 1 for a turbine with a blade, achieved at the blade root or blade platform increased cooling and a relatively high heat flow can be dissipated. It is another object of the invention to provide a manufacturing method for such a blade.
  • This first object is inventively achieved in that a plurality of turbulators is formed on at least one of the walls of the cooling channel of a paddle wheel according to the invention, which are designed such that they increase the turbulence of a cooling fluid flowing through the cooling channel.
  • the cooling fluid does not flow along more or less smooth walls in the cooling channel extending between the outer periphery of the wheel disc and the underside of the platform of the blade in the at least one cooling channel extending axially or in the main flow direction of a hot gas but it is specifically provided a plurality of turbulators or turbulence elements, which are formed on at least one of the walls of the cooling channel and increase the turbulence of the cooling fluid within the cooling passage.
  • turbulators With these turbulators, the heat transfer between the swirling cooling fluid and all walls, but especially the turbulators associated wall of the cooling channel is increased and thereby cooled the blade root reinforced.
  • the turbulators or turbulence elements are adapted in accordance with the desired heat transfer, so that targeted a maximum hot gas side material temperature and the cooling fluid flow through the cooling channel can be dimensioned accordingly to the associated blade.
  • turbulators ribs or nipples or dimples can be used.
  • the plurality of turbulators is advantageously formed on the underside of a platform of the blade root.
  • the plurality of turbulators is advantageously designed in the form of pockets, which are formed in the at least one wall of the cooling channel forming material. Such pockets can also be subsequently formed in existing blades and thus the invention desired enlargement of the heat transfer at the blade root can be achieved.
  • the turbulators or pockets are also advantageously aligned in each case substantially transversely or obliquely to the flow direction of the cooling fluid flowing through the cooling channel. Such turbulators lead to a particularly strong turbulence of cooling fluid flowing in the cooling channel.
  • a particularly good and uniform cooling of the platform can be achieved if the turbulators are aligned obliquely to the flow direction of the cooling fluid flowing through the cooling channel, that they deflect the flowing cooling fluid in the direction of a neck of the blade root.
  • the flow through the cross-section usually wedge-shaped or triangular cooling channel can be selectively adjusted.
  • the number of turbulators or pockets provided per unit area should be increased in comparison to areas of lower heat load in such areas of increased heat load.
  • the blade root of at least one blade should also advantageously be designed with a platform on each of which a cooling channel is located along an elongated neck of the blade root and the plurality of turbulators in the form of a cooling channel on the underside of the platform extending series is designed.
  • paddle wheels can be upgraded without much structural change for use at higher temperatures.
  • the turbulators according to the invention can also be formed in an operation forming the blade and in particular its blade, so that almost no additional effort is required for its production.
  • the turbulators can be formed in a separate operation after at least one operation forming the blade and in particular its blade.
  • paddle wheels of existing turbines in According to the invention be retrofitted with turbulators or pockets, which lead to the above-described improved heat transfer at the blade root.
  • a blade for a blade wheel of a turbine in particular a gas turbine, which is provided with a flowable by a hot gas blade and a blade root having a platform, which, based on the main flow direction of the hot gas, extending from an upstream edge to a downstream edge along a platform longitudinal edge and at which a neck and farther away teeth are disposed on a lower side of the airfoil, and at the side remote from the airfoil bottom of the platform laterally of the neck along the Platform longitudinal edge a plurality of turbulators are formed, which are designed such that they increase the turbulence of a flowing along the bottom cooling fluid in the installed state of the blade.
  • the plurality of turbulators on such a bucket should be in the form of pockets formed in the material of the platform.
  • the turbulators are formed in a the blade forming operation with.
  • the turbulators are thus mitgeformt directly in the re-production of the blade.
  • an existing and used blade can be retrofitted during an inspection incident of the gas turbine with the turbulators by this in a separate operation after at least one Shovel sheet forming operation are formed. In this way, the service life of the blade can be further increased while saving of cooling air, which also has a positive effect on the efficiency of the gas turbine.
  • FIG. 1 a blade 10 is illustrated according to the prior art, which has a blade root 12 and an adjoining blade 14.
  • the blade root 12 is designed as a fir tree root with a platform 16 on which a neck 18 and farther away teeth 20 are arranged on the side opposite the blade blade 14.
  • the platform 16, the neck 18 and the teeth 20 are designed as an elongated profile, which is arranged with a built-in blade 10 in a groove (not shown) of a wheel disc 22 of a turbine rotor and there is provided for holding the blade 14 and for receiving in particular its centrifugal forces ,
  • Such an installation position of a blade 10 on a wheel disc 22 is basically in FIG. 3 illustrated.
  • the neck 18 and the teeth 20 facing bottom of the Platform 16 provided with a substantially smooth surface.
  • the bottom 24 is, however, designed with a plurality of turbulators 26, which may each be arranged in a row on both sides of the neck 18.
  • the turbulators 26 face a cooling channel 28 extending in the main flow direction of a hot gas, which is provided between the underside 24 of the platform 16 and the outer periphery of the wheel disc 22.
  • the cooling channel 28 extends along a platform longitudinal edge, which extends from an upstream edge of the platform 16 to a downstream edge, with respect to the main flow direction of the hot gas flowing through the gas turbine during operation.
  • the cooling channel 28 flows through a cooling fluid, not shown, in a flow direction 30.
  • the turbulators 26 are arranged only along the platform longitudinal edge and with respect to this flow of the cooling fluid transversely or obliquely to the flow direction 30 designed as pockets which are formed in the material of the platform 16, and to the underside 24 each having an opening. In these pockets there is an additional turbulence of the cooling fluid flowing through the cooling channel 28 and thus to an improved heat transfer from the platform 16 into the cooling fluid. Thus, the pockets lead to increased heat dissipation and improved cooling of the blade root 12 and the platform 16.
  • the airfoil 14 has a pressure-side wall 27.
  • the embodiment with turbulators 26 arranged on the underside leads to advantages. If one of the two platform longitudinal edges, for example, the pressure side platform side relative to the airfoil 14 in the circumferential direction of the wheel disc 22 further protrudes than the other of the example is the suction side platform side, it is sufficient that only on the pressure side platform longitudinal edge on the Bottom 24 turbulators 26 are provided as in FIG. 3 shown, which swirl the cooling fluid in the cooling channel 28 and thus also allow for the suction-side platform longitudinal edge 29b of the immediately adjacent turbine blade 10 of the impeller a sufficiently high heat transfer in relation to the prior art.
  • the pockets of the turbulators 26 may, for example, be anodized into the material of the platform 16 and advantageously have a length which corresponds approximately to two to seven times, in particular three to five times, particularly advantageously four times the width of a pocket.
  • the turbulators 26 may also be designed in the form of nipples or dimples on the underside 24 of the platform 16. With such turbulators 26 slots or webs are respectively formed on the underside 24, which represent partial flow resistance for the flowing through the cooling channel 28 cooling fluid and thus lead to turbulence within the cooling fluid.
  • the turbulators 26 are preferably oriented obliquely to the flow of cooling fluid so as to divert the cooling fluid from a gap formed by two endwise opposed platforms 16 of adjacent turbine blades 10.
  • the cooling fluid from the turbulators 26 is also guided against the neck 18 of the blade root 12.
  • FIG. 3 is shown below the platform 16 existing cross-section of the cooling channel 28th wedge-shaped, ie from the platform edge, the radial height of the cross-section decreases towards the neck 18 of the blade root 12.
  • the cooling fluid would flow without such inclined turbulators 26 due to the locally lower flow resistance increasingly in the larger cross-sectional area than in the neck close, smaller cross-sectional area.
  • additional material may be deposited on the underside 24 of the platform 16 for the turbulators 26 by build-up welding. This additional material is then at least partially removed in a subsequent step by suitable methods, so as to form the turbulators 26.
  • a prefabricated, separate module with turbulators 26 in a separate operation from the (cast) production of the turbine blade can also be inexpensively fastened by positive and / or positive connection.
  • Prefabricated modules can be retrofitted for inspection work in a time-saving manner.
  • the turbulator module may for example have the same longitudinal extent as the platform longitudinal edge and, equipped with a tongue and groove configuration, frontally into the platform 16 in one along the Bottom 24 extending corresponding recess be inserted to be subsequently fixed by welding or soldering.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)

Claims (15)

  1. Roue à aubes d'une turbine,
    comprenant au moins une aube ( 10 ) sur laquelle peut passer un gaz chaud, dont une emplanture ( 12 ) comportant une plate-forme ( 16 ) est maintenue sur un disque ( 22 ) de roue et dans laquelle un canal ( 28 ) de refroidissement s'étendant dans la direction d'écoulement principal du gaz chaud se trouve entre le pourtour extérieur du disque ( 22 ) de roue et la plate-forme ( 16 ) de l'aube,
    caractérisée en ce que
    sur au moins l'une des parois du canal ( 28 ) de refroidissement est constituée une pluralité de dispositifs ( 26 ) donnant de la turbulence, qui sont conformés de manière à augmenter la turbulence d'un fluide de refroidissement s'écoulant dans le canal ( 28 ) de refroidissement.
  2. Roue à aubes suivant la revendication 1,
    caractérisée en ce que
    la pluralité de dispositifs ( 26 ) donnant de la turbulence est formée sur le côté ( 24 ) inférieur de la plate-forme ( 16 ) de l'emplanture ( 12 ) de l'aube.
  3. Roue à aubes suivant la revendication 1 ou 2,
    caractérisé en ce que
    la pluralité de dispositifs ( 26 ) donnant de la turbulence est conformée sous la forme de poches, qui sont en le matériau formant la au moins une paroi du canal ( 28 ) de refroidissement.
  4. Roue à aubes suivant l'une des revendications précédentes,
    caractérisée en ce que les dispositifs ( 26 ) donnant de la turbulence sont dirigés respectivement sensiblement transversalement ou de façon inclinée par rapport à la direction ( 30 ) d'écoulement du fluide de refroidissement s'écoulant dans le canal ( 28 ) de refroidissement.
  5. Roue à aubes suivant l'une des revendications précédentes,
    caractérisée en ce que
    les dispositifs ( 26 ) donnant de la turbulence sont inclinés par rapport à la direction ( 30 ) d'écoulement du fluide de refroidissement s'écoulant dans le canal ( 28 ) de refroidissement de manière à ce que fluide de refroidissement qui s'écoule soit dévié dans la direction d'un col ( 18 ) de l'emplanture ( 12 ) de l'aube.
  6. Roue à aubes suivant l'une des revendications précédentes,
    caractérisée en ce que
    dans au moins une partie sollicitée davantage thermiquement de la roue à aubes, le nombre des dispositifs ( 26 ) donnant de la turbulence prévue par unité de surface est augmentée par rapport à au moins une partie moins soumise à la chaleur.
  7. Roue à aubes suivant l'une des revendications précédentes,
    caractérisée en ce que l'emplanture ( 12 ) d'au moins une aube ( 10 ) est conformée en ayant une plate-forme ( 16 ) sur laquelle se trouve le long d'un col ( 18 ) s'étendant en longueur de part et d'autre respectivement un canal ( 28 ) de refroidissement et la pluralité de dispositifs ( 26 ) donnant de la turbulence est sous la forme d'une rangée s'étendant, dans le canal ( 28 ) de refroidissement associé, sur le côté ( 24 ) inférieur de la plate-forme ( 16 ).
  8. Roue à aubes suivant l'une des revendications précédentes,
    caractérisée en ce que
    les dispositifs ( 26 ) donnant de la turbulence ont été formés dans une passe opératoire formant l'aube ( 10 ) et notamment sa lame ( 14 ) .
  9. Roue à aubes suivant l'une des revendications précédentes, caractérisée en ce que
    les dispositifs ( 26 ) donnant de la turbulence ont été formés dans une passe opératoire distincte après au moins une passe opératoire formant l'aube ( 10 ) et notamment sa lame ( 14 ).
  10. Aube ( 10 ) pour une roue à aubes d'une turbine, notamment d'une turbine à gaz, comprenant une lame ( 14 ) d'aube sur laquelle peut passer un gaz chaud et une emplanture ( 12 ) d'aube qui a une plate-forme ( 16 ) laquelle, rapportée à la direction principale d'écoulement du gaz chaud, s'étend d'un bord ( 31 ) d'attaque à un bord ( 33 ) de fuite le long d'un bord ( 29 ) longitudinal de la plate-forme et sur laquelle sont montés, sur un côté ( 24 ) inférieur opposé à la lame ( 14 ) de l'aube, un col ( 18 ) et plus loin des dents ( 20 ), une pluralité de dispositifs ( 26 ) donnant de la turbulence étant formée du côté ( 24 ) inférieur de la plate-forme ( 16 ) et étant conformée de façon à augmenter, à l'état monté de l'aube ( 10 ), la turbulence d'un fluide de refroidissement s'écoulant le long du côté ( 24 ) inférieur,
    caractérisée en ce que
    les dispositifs ( 26 ) donnant de la turbulence sont disposés latéralement au col ( 18 ) le long du bord ( 29 ) longitudinal de la plate-forme.
  11. Aube ( 10 ) suivant la revendication 10,
    caractérisée en ce que
    la pluralité de dispositifs ( 26 ) donnant de la turbulence est formée sous la forme de poches qui sont en le matériau de la plate-forme ( 16 ).
  12. Aube ( 10 ) suivant la revendication 10 ou 11,
    caractérisée en ce que
    les dispositifs ( 28 ) donnant de la turbulence sont inclinés par rapport à la direction d'écoulement du fluide de refroidissement s'écoulant le long du bord ( 29 ) longitudinal de la plate-forme de manière à ce qu'ils dévient, au moins en partie dans la direction du col ( 18 ) de l'emplanture ( 16 ) de l'aube, le fluide de refroidissement qui s'écoule.
  13. Procédé de fabrication d'une aube ( 10 ) suivant l'une des revendications 10, 11 ou 12,
    caractérisé en ce que
    on forme des dispositifs ( 26 ) donnant de la turbulence dans la même passe opératoire que celle où l'on forme la lame ( 14 ) de l'aube.
  14. Procédé de fabrication d'une aube ( 10 ) suivant l'une des revendications 10, 11 ou 12,
    caractérisé en ce que
    l'on forme des dispositifs ( 26 ) donnant de la turbulence dans une passe opératoire distincte après au moins une passe opératoire formant la lame ( 14 ) de l'aube.
  15. Procédé de fabrication suivant la revendication 14,
    caractérisé en ce que
    l'on fabrique à l'avance les dispositifs ( 26 ) donnant de la turbulence sur un module séparé, lequel module est fixé dans une passe opératoire distincte au côté ( 24 ) inférieur de la plate-forme ( 16 ) par complémentarité de forme et/ou par complémentarité de force.
EP05766734A 2004-07-09 2005-06-13 Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant Active EP1766192B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP05766734A EP1766192B1 (fr) 2004-07-09 2005-06-13 Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant
PL05766734T PL1766192T3 (pl) 2004-07-09 2005-06-13 Koło łopatkowe turbiny z łopatką i co najmniej jednym kanałem chłodzącym

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04016237A EP1614861A1 (fr) 2004-07-09 2004-07-09 Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme
EP05766734A EP1766192B1 (fr) 2004-07-09 2005-06-13 Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant
PCT/EP2005/052714 WO2006005659A1 (fr) 2004-07-09 2005-06-13 Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant

Publications (2)

Publication Number Publication Date
EP1766192A1 EP1766192A1 (fr) 2007-03-28
EP1766192B1 true EP1766192B1 (fr) 2011-01-12

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP04016237A Withdrawn EP1614861A1 (fr) 2004-07-09 2004-07-09 Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme
EP05766734A Active EP1766192B1 (fr) 2004-07-09 2005-06-13 Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP04016237A Withdrawn EP1614861A1 (fr) 2004-07-09 2004-07-09 Roue de turbine comprenant des aubes de turbine avec turbulateurs sur la surface radiale interne de la plate-forme

Country Status (9)

Country Link
US (1) US7758309B2 (fr)
EP (2) EP1614861A1 (fr)
JP (1) JP4637906B2 (fr)
CN (1) CN101014752B (fr)
AT (1) ATE495347T1 (fr)
DE (1) DE502005010841D1 (fr)
ES (1) ES2358336T3 (fr)
PL (1) PL1766192T3 (fr)
WO (1) WO2006005659A1 (fr)

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FR2961845B1 (fr) * 2010-06-28 2013-06-28 Snecma Propulsion Solide Aube de turbomachine a geometrie complementaire paire/impaire et son procede de fabrication
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US10001013B2 (en) * 2014-03-06 2018-06-19 General Electric Company Turbine rotor blades with platform cooling arrangements
US10364684B2 (en) 2014-05-29 2019-07-30 General Electric Company Fastback vorticor pin
EP3149279A1 (fr) 2014-05-29 2017-04-05 General Electric Company Générateur de turbulence fastback
US10233775B2 (en) 2014-10-31 2019-03-19 General Electric Company Engine component for a gas turbine engine
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JP2008506061A (ja) 2008-02-28
CN101014752A (zh) 2007-08-08
ES2358336T3 (es) 2011-05-09
WO2006005659A1 (fr) 2006-01-19
US7758309B2 (en) 2010-07-20
PL1766192T3 (pl) 2011-06-30
DE502005010841D1 (de) 2011-02-24
US20080267784A1 (en) 2008-10-30
EP1614861A1 (fr) 2006-01-11
ATE495347T1 (de) 2011-01-15
CN101014752B (zh) 2011-06-08
EP1766192A1 (fr) 2007-03-28
JP4637906B2 (ja) 2011-02-23

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