US20040001753A1 - Air and steam cooled platform of a turbine blade or vane - Google Patents

Air and steam cooled platform of a turbine blade or vane Download PDF

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Publication number
US20040001753A1
US20040001753A1 US10/418,158 US41815803A US2004001753A1 US 20040001753 A1 US20040001753 A1 US 20040001753A1 US 41815803 A US41815803 A US 41815803A US 2004001753 A1 US2004001753 A1 US 2004001753A1
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US
United States
Prior art keywords
vane
cooling
turbine blade
platform
air
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.)
Abandoned
Application number
US10/418,158
Inventor
Peter Tiemann
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
Application filed by Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: OLTMANNS, IRIS, LEGAL CUSTODIAN FOR PETER TIEMANN
Publication of US20040001753A1 publication Critical patent/US20040001753A1/en
Abandoned 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
    • F01D5/18—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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • 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
    • 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
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • 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
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the present invention generally relates to a cooled platform of a turbine blade or vane.
  • EP 1 126 134 A1 discloses an air and steam cooled main blade or vane part of a turbine blade or vane.
  • U.S. Pat. No. 5,829,245 discloses a platform of a turbine blade or vane which is either steam or air cooled.
  • the present invention is based on the discovery that the steam cooling can be used for regions which are simple to cool, whereas the air cooling can be used for regions which are more difficult to cool and, furthermore, can lead to convective cooling of the bores and to film cooling.
  • the outer region is advantageously air cooled, whereas the inner region is steam cooled. Therefore, the platform according to the invention is simultaneously air cooled and steam cooled.
  • the steam cooling saves on compressed air for cooling.
  • the cooling action can be intensified in both the outer region and the inner region and with air and steam cooling by carrying out impingement cooling, in particular using impingement-cooling inserts.
  • FIG. 1 diagrammatically depicts a longitudinal section through a platform of a turbine blade or vane
  • FIG. 2 illustrates a planned view of a platform of the turbine blade or vane.
  • FIG. 1 shows part of a turbine blade or vane 1 , in particular a gas turbine blade or vane 1 , with, for example, a rectangular platform 4 (FIG. 2) in longitudinal section (section perpendicular to the plane of the drawing in FIG. 2).
  • the turbine blade or vane 1 has a main blade or vane region 7 with a main blade or vane cavity 10 in which, by way of example, air cooling and steam cooling of the main blade or vane region 7 takes place.
  • a plurality of turbine blades or vanes 1 are arranged in a turbine and are connected to one another, for example, by a connecting/sealing element 22 in the region of platform 4 .
  • the platform 4 has an outer region 28 (FIG. 2, indicated by dashed lines), which is formed along an outer periphery 29 of the platform 4 .
  • the outer region 28 of the platform 4 surrounds an inner region 25 of the platform 4 .
  • the outer region 28 is, for example, air cooled.
  • the air is taken, for example, from the turbine compressed air.
  • impingement-cooling insert 13 a In the outer region 28 there is, for example, at least one impingement-cooling insert 13 a in order to intensify the cooling action.
  • the impingement-cooling insert 13 a engages, for example, in a recess in the platform 4 , i.e. in an air cooling cavity 16 , the air cooling cavity 16 being arranged on that side of the platform 4 which is remote from the main blade or vane region 7 , i.e. the underside 5 .
  • impingement-cooling insert 13 a there is at least one impingement air passage 31 , through which air flows into the air cooling cavity 16 .
  • the direction of flow is indicated by arrows 37 , the cooling air flowing from the underside 5 of the platform 4 toward an outer side 6 which is located in an outer region 40 .
  • the impingement-cooling insert 13 a produces impingement cooling of the platform 4 in the outer region 28 in a region of the outer side 6 which is subject to thermal loads.
  • the air cooling cavity 16 there is, for example, at least one air passage 34 , in particular a film cooling opening 34 , in the platform 4 , through which the cooling air flows out of the air cooling cavity 16 into the outer region 40 surrounding the blade or vane 1 .
  • the air passage 34 is designed as a film cooling bore, resulting in film cooling of the platform 4 .
  • the air cooling therefore forms, for example, an open system, since the air is not returned to the compressed air.
  • the outer region 28 is separated from the inner region 25 by a separating rib 57 which, by way of example, runs all the way around the underside 5 in the platform 4 .
  • the steam cooling takes place in the inner region 25 of the platform 4 below the main blade or vane cavity 10 of the turbine blade or vane 1 .
  • the inner region 25 there is, for example, an impingement-cooling insert 13 d which engages in a corresponding recess 19 , a steam cooling cavity 19 , in the platform 4 .
  • the steam flows out of the steam cooling cavity 19 through a steam passage 52 in the platform 4 , for example into the main blade or vane cavity 10 before flowing back into the steam circuit through a steam return passage 55 , so that the steam cooling forms a closed circuit.
  • a cover 59 forms the steam reservoir 43 , for example together with the impingement-cooling insert 13 d.
  • the impingement-cooling insert 13 d of the inner region 25 and the impingement-cooling insert 13 a of the outer region 28 may also be formed integrally.
  • the impingement-cooling inserts 13 a, 13 d rest on the separating rib 57 and are secured to it, for example by welding.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

A turbine blade or vane includes a platform that is cooled by way of air and steam. The air cooling may form an open circuit, where the steam cooling may form a closed circuit.

Description

  • The present application hereby claims priority under 35 U.S.C. §119 on German patent application number 10217388.5, filed Apr. 18, 2002, the entire contents of which are hereby incorporated herein by reference.[0001]
    • FIELD OF THE INVENTION
  • The present invention generally relates to a cooled platform of a turbine blade or vane. [0002]
    • BACKGROUND OF THE INVENTION
  • [0003] EP 1 126 134 A1 discloses an air and steam cooled main blade or vane part of a turbine blade or vane.
  • U.S. Pat. No. 5,829,245 discloses a platform of a turbine blade or vane which is either steam or air cooled. [0004]
  • The complete cooling or a turbine blade or vane including main blade or vane region and platform and/or the root region by means of steam cooling requires a high design outlay, entailing cost problems. Although complete air cooling is possible, it leads to a higher loss of compressed air as a result of the compressed air which is removed in order to provide the cooling air. [0005]
    • SUMMARY OF THE INVENTION
  • It is an object of the present invention to provide a platform for a turbine blade or vane which is cooled and can be produced at low cost. [0006]
  • The present invention is based on the discovery that the steam cooling can be used for regions which are simple to cool, whereas the air cooling can be used for regions which are more difficult to cool and, furthermore, can lead to convective cooling of the bores and to film cooling. [0007]
  • In this context, it is advantageous if the steam cooling has a closed circuit. [0008]
  • Since the more critical region to be cooled is in the outer region of the platform, the outer region is advantageously air cooled, whereas the inner region is steam cooled. Therefore, the platform according to the invention is simultaneously air cooled and steam cooled. The steam cooling saves on compressed air for cooling. [0009]
  • The cooling action can be intensified in both the outer region and the inner region and with air and steam cooling by carrying out impingement cooling, in particular using impingement-cooling inserts. [0010]
  • If a single piece impingement-cooling insert is used, the number of parts which have to be fitted is reduced. [0011]
  • Further scope of applicability of the present invention will become apparent from the detailed description given hereinafter. However, it should be understood that the detailed description and specific examples, while indicating exemplary embodiments of the present invention, are given by way of illustration only, since various changes and modifications within the spirit and scope of the invention will become apparent to those skilled in the art from this detailed description.[0012]
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • The present invention will become more fully understood from the detailed description given hereinbelow and the accompanying drawings which are given by way of illustration only, and thus are not limitative of the present invention, and wherein: [0013]
  • FIG. 1 diagrammatically depicts a longitudinal section through a platform of a turbine blade or vane; and [0014]
  • FIG. 2 illustrates a planned view of a platform of the turbine blade or vane.[0015]
    • DETAILED DESCRIPTION OF THE EXEMPLARY EMBODIMENTS
  • FIG. 1 shows part of a turbine blade or [0016] vane 1, in particular a gas turbine blade or vane 1, with, for example, a rectangular platform 4 (FIG. 2) in longitudinal section (section perpendicular to the plane of the drawing in FIG. 2).
  • The turbine blade or [0017] vane 1 has a main blade or vane region 7 with a main blade or vane cavity 10 in which, by way of example, air cooling and steam cooling of the main blade or vane region 7 takes place.
  • A plurality of turbine blades or [0018] vanes 1 are arranged in a turbine and are connected to one another, for example, by a connecting/sealing element 22 in the region of platform 4.
  • The [0019] platform 4 has an outer region 28 (FIG. 2, indicated by dashed lines), which is formed along an outer periphery 29 of the platform 4. The outer region 28 of the platform 4 surrounds an inner region 25 of the platform 4. The outer region 28 is, for example, air cooled. The air is taken, for example, from the turbine compressed air.
  • In the [0020] outer region 28 there is, for example, at least one impingement-cooling insert 13 a in order to intensify the cooling action. The impingement-cooling insert 13 a engages, for example, in a recess in the platform 4, i.e. in an air cooling cavity 16, the air cooling cavity 16 being arranged on that side of the platform 4 which is remote from the main blade or vane region 7, i.e. the underside 5.
  • In the impingement-cooling insert [0021] 13 a there is at least one impingement air passage 31, through which air flows into the air cooling cavity 16. The direction of flow is indicated by arrows 37, the cooling air flowing from the underside 5 of the platform 4 toward an outer side 6 which is located in an outer region 40.
  • The impingement-[0022] cooling insert 13a produces impingement cooling of the platform 4 in the outer region 28 in a region of the outer side 6 which is subject to thermal loads.
  • Starting from the [0023] air cooling cavity 16 there is, for example, at least one air passage 34, in particular a film cooling opening 34, in the platform 4, through which the cooling air flows out of the air cooling cavity 16 into the outer region 40 surrounding the blade or vane 1. In this case, by way of example, the air passage 34 is designed as a film cooling bore, resulting in film cooling of the platform 4. The air cooling therefore forms, for example, an open system, since the air is not returned to the compressed air.
  • The [0024] outer region 28 is separated from the inner region 25 by a separating rib 57 which, by way of example, runs all the way around the underside 5 in the platform 4.
  • The steam cooling takes place in the [0025] inner region 25 of the platform 4 below the main blade or vane cavity 10 of the turbine blade or vane 1. In the inner region 25 there is, for example, an impingement-cooling insert 13 d which engages in a corresponding recess 19, a steam cooling cavity 19, in the platform 4. Steam flows out of a steam circuit of the turbine into a steam reservoir 43 through a steam inlet opening 46, in order to flow into the steam cooling cavity 19 through at least one impingement steam passage 49 which is present. This produces impingement cooling of the platform 4 in the inner region 25.
  • The steam flows out of the [0026] steam cooling cavity 19 through a steam passage 52 in the platform 4, for example into the main blade or vane cavity 10 before flowing back into the steam circuit through a steam return passage 55, so that the steam cooling forms a closed circuit.
  • Other connections between [0027] steam cooling cavity 19 and steam return passage 55 without connection to the main blade or vane cavity 10 are also conceivable.
  • A [0028] cover 59 forms the steam reservoir 43, for example together with the impingement-cooling insert 13 d.
  • The impingement-cooling insert [0029] 13d of the inner region 25 and the impingement-cooling insert 13 a of the outer region 28 may also be formed integrally.
  • The impingement-cooling inserts [0030] 13 a, 13 d, by way of example, rest on the separating rib 57 and are secured to it, for example by welding.
  • Exemplary embodiments being thus described, it will be obvious that the same may be varied in many ways. Such variations are not to be regarded as a departure from the spirit and scope of the present invention, and all such modifications as would be obvious to one skilled in the art are intended to be included within the scope of the following claims. [0031]

Claims (20)

What is claimed is:
1. A turbine blade or vane, comprising:
a platform being both air and steam cooled.
2. The turbine blade or vane as claimed in claim 1, wherein the air cooling forms an open circuit.
3. The turbine blade or vane as claimed in claim 1, wherein the steam cooling forms a closed circuit.
4. The turbine blade or vane as claimed in claim 1, wherein the platform is air cooled in an outer region.
5. The turbine blade or vane as claimed in claim 1, wherein an inner region of the platform is steam cooled.
6. The turbine blade or vane as claimed in claim 4, wherein the cooling in the outer region is affected by impingement cooling.
7. The turbine blade or vane as claimed in claim 5, wherein the cooling in the inner region is affected by impingement cooling.
8. The turbine blade or vane as claimed in claim 6, wherein the platform includes at least one impingement cooling insert.
9. The turbine blade or vane as claimed in claim 6, wherein the outer region has at least one impingement cooling insert.
10. The turbine blade or vane as claimed in claim 7, wherein the inner region has at least one impingement cooling insert.
11. The turbine blade or vane as claimed in claim 1, wherein film cooling of the platform is affected by the air cooling by way of at least one film cooling bore.
12. The turbine blade or vane as claimed in claim 9, wherein the impingement-cooling insert of the inner region and the impingement-cooling insert of the outer region are formed integrally.
13. The turbine blade or vane as claimed in claim 2, wherein the platform is air cooled in an outer region.
14. The turbine blade or vane as claimed in claim 2, wherein an inner region of the platform is steam cooled.
15. The turbine blade or vane as claimed in claim 3, wherein an inner region of the platform is steam cooled.
16. The turbine blade or vane as claimed in claim 7, wherein the platform includes at least one impingement cooling insert.
17. The turbine blade or vane as claimed in claim 10, wherein the impingement-cooling insert of the inner region and the impingement-cooling insert of the outer region are formed integrally.
18. The turbine blade or vane as claimed in claim 2, wherein the steam cooling forms a closed circuit.
19. The turbine blade or vane as claimed in claim 4, wherein an inner region of the platform is steam cooled.
20. The turbine blade or vane as claimed in claim 18, wherein the platform is air cooled in an outer region and wherein an inner region of the platform is steam cooled.
US10/418,158 2002-04-18 2003-04-18 Air and steam cooled platform of a turbine blade or vane Abandoned US20040001753A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10217388.5 2002-04-18
DE10217388A DE10217388A1 (en) 2002-04-18 2002-04-18 Air and steam-cooled platform of a turbine blade

Publications (1)

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US20040001753A1 true US20040001753A1 (en) 2004-01-01

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US10/418,158 Abandoned US20040001753A1 (en) 2002-04-18 2003-04-18 Air and steam cooled platform of a turbine blade or vane

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US (1) US20040001753A1 (en)
EP (1) EP1355040A3 (en)
JP (1) JP2003314204A (en)
CN (1) CN1451847A (en)
DE (1) DE10217388A1 (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070048122A1 (en) * 2005-08-30 2007-03-01 United Technologies Corporation Debris-filtering technique for gas turbine engine component air cooling system
US20080025842A1 (en) * 2006-07-27 2008-01-31 Siemens Power Generation, Inc. Turbine vane with removable platform inserts
US20090053037A1 (en) * 2006-07-27 2009-02-26 Siemens Power Generation, Inc. Turbine vanes with airfoil-proximate cooling seam
US20100054932A1 (en) * 2008-09-03 2010-03-04 Siemens Power Generation, Inc. Circumferential Shroud Inserts for a Gas Turbine Vane Platform
US20120063891A1 (en) * 2009-03-30 2012-03-15 Alstom Technology Ltd Cooled component for a gas turbine
US8840370B2 (en) 2011-11-04 2014-09-23 General Electric Company Bucket assembly for turbine system
US20180311740A1 (en) * 2017-04-26 2018-11-01 General Electric Company Method of providing cooling structure for a component
US10502093B2 (en) * 2017-12-13 2019-12-10 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10533454B2 (en) 2017-12-13 2020-01-14 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10570773B2 (en) 2017-12-13 2020-02-25 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10895156B2 (en) * 2016-08-25 2021-01-19 Siemens Aktiengesellschaft Turbomachine arrangement with a platform cooling device for a blade of a turbomachine

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* Cited by examiner, † Cited by third party
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US8845289B2 (en) * 2011-11-04 2014-09-30 General Electric Company Bucket assembly for turbine system
GB202213804D0 (en) * 2022-09-22 2022-11-09 Rolls Royce Plc Platform for stator vane
GB202213805D0 (en) * 2022-09-22 2022-11-09 Rolls Royce Plc Platform for stator vane

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US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
US5829245A (en) * 1996-12-31 1998-11-03 Westinghouse Electric Corporation Cooling system for gas turbine vane
US6402463B2 (en) * 1999-07-16 2002-06-11 General Electric Company Pre-stressed/pre-compressed gas turbine nozzle
US6406254B1 (en) * 1999-05-10 2002-06-18 General Electric Company Cooling circuit for steam and air-cooled turbine nozzle stage
US6431824B2 (en) * 1999-10-01 2002-08-13 General Electric Company Turbine nozzle stage having thermocouple guide tube

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US5320483A (en) * 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
JP3316405B2 (en) * 1997-02-04 2002-08-19 三菱重工業株式会社 Gas turbine cooling vane
JP3411775B2 (en) * 1997-03-10 2003-06-03 三菱重工業株式会社 Gas turbine blade
CA2231988C (en) * 1998-03-12 2002-05-28 Mitsubishi Heavy Industries, Ltd. Gas turbine blade
EP1126134A1 (en) * 2000-02-17 2001-08-22 Siemens Aktiengesellschaft Air and steam-cooled gas turbine vane

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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
US5829245A (en) * 1996-12-31 1998-11-03 Westinghouse Electric Corporation Cooling system for gas turbine vane
US6406254B1 (en) * 1999-05-10 2002-06-18 General Electric Company Cooling circuit for steam and air-cooled turbine nozzle stage
US6402463B2 (en) * 1999-07-16 2002-06-11 General Electric Company Pre-stressed/pre-compressed gas turbine nozzle
US6431824B2 (en) * 1999-10-01 2002-08-13 General Electric Company Turbine nozzle stage having thermocouple guide tube

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070048122A1 (en) * 2005-08-30 2007-03-01 United Technologies Corporation Debris-filtering technique for gas turbine engine component air cooling system
US20080025842A1 (en) * 2006-07-27 2008-01-31 Siemens Power Generation, Inc. Turbine vane with removable platform inserts
US7488157B2 (en) 2006-07-27 2009-02-10 Siemens Energy, Inc. Turbine vane with removable platform inserts
US20090053037A1 (en) * 2006-07-27 2009-02-26 Siemens Power Generation, Inc. Turbine vanes with airfoil-proximate cooling seam
US7581924B2 (en) 2006-07-27 2009-09-01 Siemens Energy, Inc. Turbine vanes with airfoil-proximate cooling seam
US20100054932A1 (en) * 2008-09-03 2010-03-04 Siemens Power Generation, Inc. Circumferential Shroud Inserts for a Gas Turbine Vane Platform
US8096758B2 (en) 2008-09-03 2012-01-17 Siemens Energy, Inc. Circumferential shroud inserts for a gas turbine vane platform
US20120063891A1 (en) * 2009-03-30 2012-03-15 Alstom Technology Ltd Cooled component for a gas turbine
US8840370B2 (en) 2011-11-04 2014-09-23 General Electric Company Bucket assembly for turbine system
US10895156B2 (en) * 2016-08-25 2021-01-19 Siemens Aktiengesellschaft Turbomachine arrangement with a platform cooling device for a blade of a turbomachine
US20180311740A1 (en) * 2017-04-26 2018-11-01 General Electric Company Method of providing cooling structure for a component
US10583489B2 (en) * 2017-04-26 2020-03-10 General Electric Company Method of providing cooling structure for a component
US10502093B2 (en) * 2017-12-13 2019-12-10 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10533454B2 (en) 2017-12-13 2020-01-14 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10570773B2 (en) 2017-12-13 2020-02-25 Pratt & Whitney Canada Corp. Turbine shroud cooling
US11118475B2 (en) 2017-12-13 2021-09-14 Pratt & Whitney Canada Corp. Turbine shroud cooling

Also Published As

Publication number Publication date
JP2003314204A (en) 2003-11-06
EP1355040A2 (en) 2003-10-22
CN1451847A (en) 2003-10-29
DE10217388A1 (en) 2003-10-30
EP1355040A3 (en) 2005-04-06

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