EP2728114B1 - Dispositif de refroidissement de plate-forme pour une aube de turbomachine - Google Patents

Dispositif de refroidissement de plate-forme pour une aube de turbomachine Download PDF

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Publication number
EP2728114B1
EP2728114B1 EP12190755.4A EP12190755A EP2728114B1 EP 2728114 B1 EP2728114 B1 EP 2728114B1 EP 12190755 A EP12190755 A EP 12190755A EP 2728114 B1 EP2728114 B1 EP 2728114B1
Authority
EP
European Patent Office
Prior art keywords
platform
blade
cooling device
cooling
platform cooling
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
EP12190755.4A
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German (de)
English (en)
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EP2728114A1 (fr
Inventor
Janos Szijarto
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
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Siemens AG
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Publication date
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Priority to EP12190755.4A priority Critical patent/EP2728114B1/fr
Publication of EP2728114A1 publication Critical patent/EP2728114A1/fr
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Publication of EP2728114B1 publication Critical patent/EP2728114B1/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
    • 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
    • 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
    • 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

Definitions

  • the present invention relates to a blade for a turbomachine and more particularly to a platform cooling device for the blade of the turbomachine.
  • the blade typically includes an airfoil portion and a root portion separated by a blade platform.
  • the airfoil portion of the blade is cooled by directing a cooling fluid to flow through radial passages formed in the airfoil portions of the blades.
  • a number of small axial passages are formed inside the blade airfoils that connect with one or more of the radial passages so that cooling air is directed over the surfaces of the airfoils, such as the leading and trailing edges or the suction and pressure surfaces. After the cooling air exits the blade it enters and mixes with the hot gas flowing through the turbine section.
  • cooling of blade platform is difficult since cooling air was not utilized in cooling the blade platform, the upper surfaces of which are exposed to the flow of hot gas from the combustors.
  • cooling of blade platform is achieved by providing film cooling by flowing a portion of the cooling air discharged from the upstream vanes over the upper surfaces of the blade root platforms, however, the film cooling is insufficient to adequately cool the blade root platform resulting in oxidation and cracking in the platforms.
  • CH703875 A2 describes a cooling device for cooling the platform of a blade of a turbo machine.
  • the device has an inlet for receiving a cooling fluid from a cooling channel of the blade.
  • the cooling fluid is directed via impingement openings to the platform to achieve an impingement cooling effect. After that, the fluid is leaving the cooling device via an outlet.
  • US patent number 6,120,249 describes a cooling concept for a gas turbine blade platform wherein cooling air passages are formed in the blade root platform which includes cavities formed in a radially inward facing surface of an overhanging surface of the blade airfoil. An impingement plate directs cooling air into these cavities for providing cooling.
  • the object is achieved by providing a platform cooling device for a blade of a turbomachine according to claim 1.
  • a platform cooling device for a blade of a turbomachine includes a first portion to be positioned at a platform of the blade, a second portion arranged at an angle to the first portion, to be positioned at a root portion of the blade, an inlet for a cooling fluid on the second portion, and a channel for directing the cooling fluid from the inlet to a plurality of impingement holes for releasing the cooling fluid at the first portion.
  • the plurality of impingement holes is present in the first portion of the platform cooling device.
  • the second portion comprises a plurality of dumping holes for the cooling fluid.
  • the dumping holes allow the cooling fluid to exit the platform cooling device into a space between the blades and from there as a leakage into the hot gas flow path.
  • the platform cooling devices includes a first protrusion at the first portion for attaching to the platform and a second protrusion at second portion for attaching to the root portion such that a cavity is formed between the device and the blade for directing the cooling fluid from the impingement holes to the dumping holes.
  • Protrusions at the first portion and the second portion allow an ease of attachment of the device with the platform and the root portion respectively. Due to the protrusions a cavity is formed between the device and the blade after attaching the platform cooling device to the platform and the root portion at the first end and the second end respectively, thereby allowing the impinged cooling fluid which gets heated after impinging on the blade platform, this heated cooling fluid is directed to the dumping holes through the cavity formed between the platform cooling device and the blade.
  • the platform cooling device is brazed at the first protrusion and the second protrusion to the blade. Brazing does not melt the base metal of the joint and allows tighter control over tolerances, hence producing a clean joint. Furthermore, brazing allows dissimilar metals to be joined. Additionally, brazing produces less thermal distortion due to uniform heating of the brazed piece.
  • the platform cooling device is formed from a nickel alloy. Nickel alloys can be easily brazed, have high strength, can withstand high temperatures and are corrosion resistant. In one embodiment, the platform cooling device is formed through laser sintering. Laser sintering technique provides an efficient way of forming a desired three dimensional shape with channels to ensure cooling effectiveness.
  • a blade for a turbo machine includes an airfoil portion and a root portion, wherein the root portion comprises a platform from which the airfoil portion extends in a radial direction, a platform cooling device disposed at the root portion, the device having a first portion and a second portion, wherein the first portion is adapted to be positioned at the platform and the second portion is adapted to be positioned at the root portion along the radial direction characterised in that the platform cooling device includes an inlet for a cooling fluid at the second portion, wherein the inlet is fluidly connected to a cooling fluid channel in the root portion, and a plurality of holes on the first portion for impinging the cooling fluid from the inlet against the platform, wherein the inlet is in flow communication with the holes for the cooling fluid.
  • the platform cooling device allows cooling fluid to be directed to portions of the platform where cooling is desired, obviating the need for making channels or cavities in the root portion of the blade.
  • the first portion of the platform cooling device is attached to the platform at a first end and the second portion of the platform cooling device is attached to the root portion at a second end. Attaching the platform cooling device at the first end and the second end allows the device to be securely fixed and also create a cavity between the platform cooling device and the blade, which allows the flow of cooling fluid.
  • the cavity extends from the first end to the second end, which allows the impinged fluid to further cool the portion of the blade in the cavity while travelling from the first end to the second end.
  • Embodiments of the present invention described below relate to a blade component in a turbo machine. However, the details of the embodiments described in the following can be transferred to a vane component without modifications, that is the terms "blade” or "vane” can be used in conjunction, since they both have the shape of an airfoil.
  • the turbomachine may include a gas turbine, a steam turbine, a turbofan and the like.
  • FIG. 1 is a schematic diagram of an exemplary blade 1 of a rotor (not shown) of a turbomachine, such as a gas turbine.
  • the blade 1 includes an airfoil portion 2 and a root portion 3.
  • the airfoil portion 2 projects from the root portion 3 in a radial direction as depicted, wherein the radial direction means a direction perpendicular to the rotation axis of the rotor.
  • the airfoil portion 2 extends radially along a longitudinal direction of the blade 1.
  • the blade 1 is attached to a body of the rotor (not shown), in such a way that the root portion 3 is attached to the body of the rotor whereas the airfoil portion 2 is located at a radially outermost position.
  • the airfoil portion 2 has an outer wall including a pressure side 6, also called pressure surface, and a suction side 7, also called suction surface.
  • the pressure side 6 and the suction side 7 are joined together along an upstream leading edge 4 and a downstream trailing edge 5, wherein the leading edge 4 and the trailing edge 5 are spaced axially from each other as depicted in FIG. 1 .
  • a platform 9 is formed at an upper portion of the root portion 3.
  • the airfoil portion 2 is connected to the platform 9 and extends in the radial direction outward from the platform 9.
  • cooling holes 8 are present on the pressure side 6 and the suction side 7 of the blade as depicted in FIG. 1 . These cooling holes 8 aid in film cooling of the blade 1.
  • the blade 1 includes a platform cooling device 10 disposed at the root portion 3 of the blade 1 for cooling the platform 9.
  • the exemplary platform cooling device 10 will be described in more detail hereinafter.
  • the platform cooling device 10 includes a first portion 11 and a second portion 12 wherein the second portion 12 is at an angle to the first portion 11.
  • angle between the first portion 11 and the second portion 12 may be from about 80 degrees to about 110 degrees.
  • first portion 11 and the second portion 12 are perpendicular to each other.
  • the platform cooling device 10 includes a first protrusion 14 at the first portion 11 and a second protrusion 16 at the second portion 12.
  • the first portion 11 of the platform cooling device 10 is adapted to be positioned at the platform 9 of the blade 1 and the second portion 12 is adapted to be positioned at the root portion 3 of the blade 1.
  • first protrusion 14 aids in attaching the first portion 11 of the platform cooling device 10 with the platform 9
  • second protrusion 16 aids in attaching the second portion 12 of the platform cooling device 10 with the root portion 3 of the blade 1.
  • An inlet 18 for a cooling fluid such as, but not limited to cooling air, is provided at the second portion 12 of the platform cooling device 10, as depicted in FIG. 2 .
  • the inlet 18 is fluidly connected to a cooling fluid channel (not shown in FIG. 2 ) in the root portion 3 of the blade 1.
  • a plurality of impingement holes 20 is present in the first portion 11 of the platform cooling device 10.
  • a channel (not shown in FIG. 2 ) within the platform cooling device 10 directs the cooling fluid from the inlet 18 to the plurality of impingement holes 20 for releasing the cooling fluid at the first portion 11. The released fluid impinges on a surface of the platform 9 thereby cooling the platform 9.
  • the platform cooling device includes a plurality of dumping holes 22 for letting out the impinged fluid from the platform cooling device 10.
  • the dumping holes 22 are located on the second portion 12 of the platform cooling device 10.
  • the platform cooling device 10 is manufactured by using laser sintering technique.
  • the platform cooling device 10 may be formed of a material which is corrosion resistant and is capable of withstanding high temperatures. More particularly, the platform cooling device 10 may be formed of a nickel based alloy.
  • FIG. 3 shows a sectional view 25 of the blade 1 depicting the root portion 3 and the platform 9 with the platform cooling device 10.
  • the platform cooling device 10 includes the first portion 11 and the second portion 12 substantially perpendicular to each other.
  • the first portion 11 is attached to the platform 9 at a first end 32 and the second portion 12 is attached to the root portion 3 at a second end 34.
  • the platform cooling device 10 is brazed with the platform 9 and the root portion 3 at the first end 32 and the second end 34 respectively.
  • the platform cooling device 10 may be attached by welding at the first end 32 and the second end 34. More particularly, brazing or welding is done at the first protrusion 14 and the second protrusion 16 thereby attaching the platform cooling device 10 at the first end 32 and the second end 34 respectively.
  • a cavity 30 is formed between the blade 1 and the platform cooling device 10 after attaching the platform cooling device 10 to the platform 9 and the root portion 3 at the first end 32 and the second end 34 respectively.
  • the platform cooling device 10 includes the first protrusion 14 and the second protrusion 16. These protrusions 14, 16 form the cavity 30 extending from the first end 32 to the second end 34.
  • the cooling fluid 27 is directed via the inlet 18 into the platform cooling device 10 from a cooling fluid channel 26 in the root portion 3. More particularly, the inlet 18 is fluidly connected to the cooling fluid channel 26 in the root portion 3 for allowing the cooling fluid 27 to enter into the platform cooling device 10. The cooling fluid 27 is directed towards the plurality of impingement holes 20 via the channel 28.
  • the cavity 30 directs the cooling fluid 27 to flow towards the second end 34.
  • the second portion 12 of the platform cooling device 10 includes the plurality of dumping holes 22.
  • the dumping holes 22 are located proximal to the second end 34 beyond the inlet 18 as depicted in FIG. 3 .
  • the cooling fluid 27 after impinging against the platform 9 flows into the cavity 30 towards the plurality of dumping holes 22.
  • the dumping holes 22 direct the fluid out from the blade into the hot gas flow path.

Landscapes

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

Claims (4)

  1. Dispositif de refroidissement de plate-forme (10) pour une pale (1) d'une turbomachine comprenant :
    - une première partie (11) à positionner au niveau d'une plate-forme (9) de la pale (1),
    - une deuxième partie (12) agencée selon un angle par rapport à la première partie (11), à positionner au niveau d'une partie de base (3) de la pale (1), la deuxième partie (12) comprenant une pluralité de trous de décharge (22) pour le fluide de refroidissement (27),
    - une admission (18) pour un fluide de refroidissement (27) sur la deuxième partie (12),
    - un canal (28) pour diriger le fluide de refroidissement (27) de l'admission (18) à une pluralité de trous de contact (20) pour libérer le fluide de refroidissement (27) au niveau de la première partie (11), la pluralité de trous de contact (20) étant présente dans la première partie (11) du dispositif de refroidissement de plate-forme (10),
    - une première saillie (14) au niveau de la première partie (11) destinée à être fixée à la plate-forme (9) à une première extrémité (32) et une deuxième saillie (16) au niveau de la deuxième partie (12) destinée à être fixée à la partie de base (3) à une deuxième extrémité (34) de telle sorte qu'une cavité (30) soit formée entre le dispositif de refroidissement de plate-forme (3) et la pale (1) après avoir fixé le dispositif de refroidissement de plate-forme (10) à la plate-forme (9) et la partie de base (3) à la première extrémité (32) et la deuxième extrémité (34) respectivement pour diriger le fluide de refroidissement (27) des trous de contact (20) aux trous de décharge (22),
    caractérisé en ce que
    les saillies (14, 16) forment la cavité (30) s'étendant de la première extrémité (32) à la deuxième extrémité (34) de telle sorte qu'une partie de la cavité (30) est formée entre le dispositif de refroidissement de plate-forme (10) et la partie de base (3) de la pale (1).
  2. Dispositif de refroidissement de plate-forme (10) selon la revendication 1, dans lequel le dispositif de refroidissement de plate-forme (10) est brasé au niveau de la première saillie (14) et de la deuxième saillie (16) à la pale (1).
  3. Dispositif de refroidissement de plate-forme (10) selon l'une quelconque des revendications 1 à 2, dans lequel le dispositif de refroidissement de plate-forme (10) est formé à partir d'un alliage de nickel.
  4. Dispositif de refroidissement de plate-forme (10) selon l'une quelconque des revendications 1 à 3, dans lequel le dispositif (10) est formé par frittage au laser.
EP12190755.4A 2012-10-31 2012-10-31 Dispositif de refroidissement de plate-forme pour une aube de turbomachine Active EP2728114B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12190755.4A EP2728114B1 (fr) 2012-10-31 2012-10-31 Dispositif de refroidissement de plate-forme pour une aube de turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12190755.4A EP2728114B1 (fr) 2012-10-31 2012-10-31 Dispositif de refroidissement de plate-forme pour une aube de turbomachine

Publications (2)

Publication Number Publication Date
EP2728114A1 EP2728114A1 (fr) 2014-05-07
EP2728114B1 true EP2728114B1 (fr) 2016-02-10

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EP12190755.4A Active EP2728114B1 (fr) 2012-10-31 2012-10-31 Dispositif de refroidissement de plate-forme pour une aube de turbomachine

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Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160146016A1 (en) * 2014-11-24 2016-05-26 General Electric Company Rotor rim impingement cooling
EP3287596A1 (fr) 2016-08-25 2018-02-28 Siemens Aktiengesellschaft Dispositif de refroidissement de plate-forme pour une aube de turbomachine et aube pour turbomachine
US20180355725A1 (en) * 2017-06-13 2018-12-13 General Electric Company Platform cooling arrangement in a turbine component and a method of creating a platform cooling arrangement

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
EP0789806B1 (fr) 1994-10-31 1998-07-29 Westinghouse Electric Corporation Pale de turbine a gaz avec plateforme refroidie
EP1028228A1 (fr) * 1999-02-10 2000-08-16 Siemens Aktiengesellschaft Dispositif de refroidissement de plate-forme d'aube rotorique de turbine
EP1413715A1 (fr) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Dispositif de refroidissement pour une plate-forme d'une aube d'une turbine à gaz
US8840369B2 (en) * 2010-09-30 2014-09-23 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades

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EP2728114A1 (fr) 2014-05-07

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