EP0911488A1 - Kühlung von statorschaufeln in gasturbinen - Google Patents

Kühlung von statorschaufeln in gasturbinen Download PDF

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Publication number
EP0911488A1
EP0911488A1 EP98917726A EP98917726A EP0911488A1 EP 0911488 A1 EP0911488 A1 EP 0911488A1 EP 98917726 A EP98917726 A EP 98917726A EP 98917726 A EP98917726 A EP 98917726A EP 0911488 A1 EP0911488 A1 EP 0911488A1
Authority
EP
European Patent Office
Prior art keywords
steam
cooling
stationary blade
passage
inner shroud
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.)
Granted
Application number
EP98917726A
Other languages
English (en)
French (fr)
Other versions
EP0911488A4 (de
EP0911488B1 (de
Inventor
Yasuoki Mitsubishi Heavy Industries Ltd. TOMITA
Sunao Mitsubishi Heavy industries Ltd. AOKI
Kiyoshi Mitsubishi Heavy Industries Ltd. SUENAGA
Tatsuo Mitsubishi Heavy Industries Ltd. ISHIGURO
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP0911488A1 publication Critical patent/EP0911488A1/de
Publication of EP0911488A4 publication Critical patent/EP0911488A4/de
Application granted granted Critical
Publication of EP0911488B1 publication Critical patent/EP0911488B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F05D2240/10—Stators
    • 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
    • F05D2260/221—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 present invention relates to a steam cooled stationary blade for a gas turbine, and more particularly to a cooled stationary blade for a gas turbine for steam cooling both an inner shroud and the blade.
  • Fig. 5 shows a typical conventional air cooled type gas turbine stationary blade.
  • numeral 40 denotes a stationary blade
  • numeral 41 denotes an outer shroud
  • numeral 42 denotes an inner shroud.
  • Reference characters 43A, 43B, 43C, 43D and 43E denote respective air passages.
  • Numeral 45 denotes a rear edge of the blade.
  • Numeral 44 denotes air blowout holes at the rear edge.
  • Reference numeral 46 denotes turbulators provided in an inner wall of each air passage 43A to 43E for enhancing heat transmission by distributing the air flow.
  • the cooling air 47 is introduced from the outer shroud 41 to the air passage 43A and flows to a base portion (at the inner shroud side).
  • the cooling air is introduced from the base portion into the next air passage 43B.
  • the cooling air flows to an upper end (at the outer shroud side) and into the next air passage 43C.
  • the cooling air flows in the same way through the air passages 43D and 43E, in that order, to thereby cool the blade.
  • the cooling air is blownout from the air blowout holes 44 of the rear edge 45, and at the same time, the rest of the air flows out from the lower side of the inner shroud 42.
  • Fig. 4 shows an example of a cooled stationary blade in which the blade is cooled by steam and the shrouds are cooled by air.
  • the steam cooling system used in this stationary blade has not yet been put into practical use. However, it is a technique which has been researched by the present applicant.
  • reference numeral 30 denotes the stationary blade, from which the outer shroud at an upper portion thereof has been omitted, and in which a portion of the blade is shown.
  • Numeral 31 denotes the inner shroud.
  • Reference numerals 33A, 33B, 33C, 33D, 33E and 33F denote steam passages of the respective interiors of the stationary blade.
  • the cooling steam 39 is introduced from a front edge portion of the outer shroud (not shown) to the steam passage 33A and from a base portion thereof (inner shroud side) into the steam passage 33B.
  • the cooling steam flows from an upper portion of the steam passage 33B (at the outer shroud side) into the next steam passage 33C and flows through the steam passages 33D and 33E in a similar manner.
  • the steam flows from the base portion side of the steam passage 33E into the steam passage 33F on the rear edge side to cool the interior of the blade. Thereafter, the steam is recovered from the steam recovery port of the outer shroud.
  • the inner shroud 31 is cooled by cooling air.
  • the cooling air 37 introduced from the lower portion of the inner shroud 31, is introduced into air cooling passages in the interior of the inner shroud 31 from one end thereof. The air flows from one side to the other within these air cooling passages to cool the entire inner shroud 31 and is discharged from the air blowout holes 38 on the other side to air cool the entire blade.
  • the air cooling system is mainly used to cool the blade, but not to cool the inner shroud at all.
  • the cooling air is introduced into the air cooling passages within the inner shroud 31 and flows from one side to the other in the inner shroud to cool the surface of the shroud from the interior.
  • the air flows out from the air blowout holes 38 on the other side.
  • a recess is formed in the inner surface of the inner shroud 31.
  • An impingement plate is provided in parallel with the inner surface of the inner shroud.
  • Another (method) also being developed by the present applicant is one in which the cooling air 37 fed from the lower portion impinges on the impingement plate and is blownout from a number of holes so that the interior of the shroud is uniformly cooled by the air.
  • a primary object of the present invention is to provide a gas turbine cooled stationary blade in which not only cooling of an interior of a blade, but also cooling of an inner shroud is performed by steam cooling, and steam that has been used for cooling is completely recovered and returned to a steam feed source for effective utilization without the necessity of cooling air to thereby enhance the efficiency of the turbine.
  • another object of the present invention is to provide a gas turbine cooled stationary blade in which the structure of a steam passage for cooling the inner shroud is simplified so that machining and assembly of the blade are also improved.
  • Fig. 1 is schematic views of a cooled stationary blade for a gas turbine in accordance with an embodiment of the present invention.
  • reference numerals 31 and 33A to 33F denote components having the same functions as those of the cooled stationary blade for the gas turbine shown in Fig. 4 now being developed by the present applicant, an explanation of which has been given so a detailed explanation will be omitted here.
  • the characteristic portion of the present invention is a cooled stationary blade for a gas turbine which is under development by the present applicant and is further improved, and not only the interior of the blade 30, but also the end portion of the inner shroud 31 is steam-cooled.
  • the cooling steam 39 is introduced into the steam passage 33A from the outer shroud (not shown) of the front edge side of the stationary blade 30 in the same way as in the example shown in Fig. 4.
  • the steam is introduced from the steam passage 33A to the steam passage 33B to flow to the upper portion thereof (at the outer shroud side) to enter the steam passage 33C.
  • the steam flows through the steam passages 33C and 33D and is introduced from the Lower portion of the steam passage 33E (on the inner shroud side) to the steam passage 33F of the rear edge of the blade 30.
  • the interior of the blade is cooled by the passage of the steam.
  • the steam is recovered from the steam recovery opening of the outer shroud (not shown) at an upper portion.
  • a portion of the cooling steam 39 that has been introduced from the steam passage 33A at the front edge is introduced into the inner shroud 31 from the lower portion of the steam passage 33A and flows from the steam introduction passage 22 to the steam passage 20 which is provided in the vicinity of an end portion of the inner shroud 31 and branches to the right and left sides from the steam introduction passage 22.
  • the steam is introduced from both sides to the steam discharge passage 21 on the rear edge side through both end portions.
  • the cooling steam that has been introduced into the steam discharge passage 21 is introduced into the steam passage 33F at the rear edge communicated with the steam discharge passage, and merges with the cooling steam that is introduced into the steam passage 33F through the steam passages 33A to 33E in the interior of the blade.
  • the (combined) steam flows upwardly and is recovered from the steam recovery opening of the outer shroud (not shown).
  • the cooling steam is used to steam cool the interior of the blade 30.
  • the end portion of the inner shroud 31 is cooled with a portion of the steam, thereby steam cooling the stationary blade as a whole.
  • Fig. 2 is a cross-sectional view showing an interior of the inner shroud 31 of the cooled blade according to the above-described embodiment.
  • the steam passage 20 is provided in a rib 35 provided in the vicinity of the end portion of the inner shroud 31.
  • the steam introduction passage 22 for communicating the steam passage 20 and the steam passage 33A with each other is provided at the front edge side of the blade.
  • the steam discharge passage 21 for communicating the steam passage 33F and the steam passage 20 with each other is provided at the rear edge side of the blade.
  • the cooling steam is introduced from the steam passage 33A on the front edge side of the stationary blade 30 through the steam introduction passage 22, as indicated by the solid lines in the drawing, to enter the steam passage 20 and is separated to the right and left to pass through both end portions of the inner shroud 31 and flow to the rear edge side of the stationary blade to cool the periphery of the inner shroud 31.
  • the steam is then discharged into the steam passage 33F from the steam discharge passage 21 at the rear edge of the stationary blade.
  • Figs. 3(a), (b) and (c) are cross-sectional views taken along the line A-A of Fig. 2 and show steam passages 20 with different respective structures.
  • a groove is first formed in a rib 35 provided at an end portion of the inner shroud 31.
  • a side plate 23 having a width which is substantially the same as that of the groove is inserted into and fixed to the groove to define the steam passage 20.
  • Fig. 3(a), (b) and (c) are cross-sectional views taken along the line A-A of Fig. 2 and show steam passages 20 with different respective structures.
  • a groove is first formed in a rib 35 provided at an end portion of the inner shroud 31.
  • a side plate 23 having a width which is substantially the same as that of the groove is inserted into and fixed to the groove to define the steam passage 20.
  • a side plate 24 having a projection with a width which is substantially the same as that of the groove and having a width which is substantially the same as an end width of the rib 35 and the inner shroud 31 is inserted into and fixed to the groove to define the steam passage 20. Furthermore, in the structure shown in Fig. 3(c), a side plate 25 having the same thickness as that of the end portion of the rib 35 and the inner shroud 31 is mounted and fixed so as to cover the entire groove formed in the rib 35 to thereby define the steam passage 20.
  • a linear welding bond, a brazing bond or the like be effected to the contact portion between the groove and the side plate as indicated by reference numeral 36 to avoid steam leakage.
  • any one of these structures may be applied to the cooled stationary blade of the gas turbine according to the present invention.
  • the structure of the steam passage 20 is not limited to these. It is also possible to cut the interior to form an integral structure. Also, the shape is not limited to rectangular, but may be formed round.
  • a structure is provided in which the steam passage 20 is formed at the peripheral portion of the end portion of the inner shroud 31, the steam is introduced from the steam passage 33A at the front edge side of the blade into the steam passage 20 through the steam introduction passage 22, and the steam passes through both side end portions of the inner shroud 31 and flows through the steam discharge passage 21 at the rear edge side of the blade from the steam passage 33F at the rear edge. Accordingly, not only the interior of the stationary blade 30, but also the inner shroud 31 may be cooled by the steam to conserve the cooling air and to reduce the power consumed by the compressor or the cooler.
  • the heat that has been absorbed by the steam due to the cooling effect may be reused in the steam feed source. Also since air is not used, it is possible to considerably enhance the efficiency of the turbine.
EP98917726A 1997-05-01 1998-04-28 Gekühlte Statorschaufel für Gasturbinen Expired - Lifetime EP0911488B1 (de)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
JP113845/97 1997-05-01
JP11384597A JP3276305B2 (ja) 1997-05-01 1997-05-01 ガスタービンの冷却静翼
JP11384597 1997-05-01
PCT/JP1998/001958 WO1998050684A1 (fr) 1997-05-01 1998-04-28 Pale fixe de refroidissement de turbine a gaz

Publications (3)

Publication Number Publication Date
EP0911488A1 true EP0911488A1 (de) 1999-04-28
EP0911488A4 EP0911488A4 (de) 2000-11-29
EP0911488B1 EP0911488B1 (de) 2004-01-28

Family

ID=14622507

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98917726A Expired - Lifetime EP0911488B1 (de) 1997-05-01 1998-04-28 Gekühlte Statorschaufel für Gasturbinen

Country Status (5)

Country Link
EP (1) EP0911488B1 (de)
JP (1) JP3276305B2 (de)
CA (1) CA2261184C (de)
DE (1) DE69821312T2 (de)
WO (1) WO1998050684A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6783323B2 (en) * 2001-07-11 2004-08-31 Mitsubishi Heavy Industries, Ltd. Gas turbine stationary blade
EP1571296A1 (de) * 2004-03-01 2005-09-07 Alstom Technology Ltd Gekühlte Strömungsmaschinenschaufel und Verfahren zur Kühlung
EP1788192A3 (de) * 2005-11-21 2008-11-12 General Electric Company Gasturbinenrotorschaufel mit gekühlter Plattformkante und Kühlverfahren für eine Plattformleitkante
EP2610436A3 (de) * 2011-12-30 2017-06-21 General Electric Company Kühlung der Plattform einer Turbinenrotorschaufel

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7147439B2 (en) * 2004-09-15 2006-12-12 General Electric Company Apparatus and methods for cooling turbine bucket platforms
JP4931157B2 (ja) * 2006-02-14 2012-05-16 株式会社Ｉｈｉ 冷却構造
JP4979983B2 (ja) * 2006-05-29 2012-07-18 三井造船株式会社 炉頂圧回収タービン翼部へのダスト付着防止装置
JP4801618B2 (ja) * 2007-03-30 2011-10-26 三菱重工業株式会社 ガスタービンの静翼およびこれを備えたガスタービン
US8684664B2 (en) * 2010-09-30 2014-04-01 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US8777568B2 (en) * 2010-09-30 2014-07-15 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US8814517B2 (en) * 2010-09-30 2014-08-26 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US8840369B2 (en) * 2010-09-30 2014-09-23 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US8858160B2 (en) * 2011-11-04 2014-10-14 General Electric Company Bucket assembly for turbine system

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04311604A (ja) * 1991-04-11 1992-11-04 Toshiba Corp タービン静翼
JPH0565802A (ja) * 1991-09-06 1993-03-19 Toshiba Corp ガスタービン
JPH0693801A (ja) * 1992-09-17 1994-04-05 Hitachi Ltd ガスタービン翼
US5320483A (en) * 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
EP0698723A2 (de) * 1994-08-23 1996-02-28 General Electric Company Geschlossener Kühlkreislauf für Turbinenleitschaufel

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2953842B2 (ja) * 1991-12-16 1999-09-27 東北電力株式会社 タービン静翼
JP3188105B2 (ja) * 1994-07-11 2001-07-16 三菱重工業株式会社 ガスタービンの動翼

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04311604A (ja) * 1991-04-11 1992-11-04 Toshiba Corp タービン静翼
JPH0565802A (ja) * 1991-09-06 1993-03-19 Toshiba Corp ガスタービン
JPH0693801A (ja) * 1992-09-17 1994-04-05 Hitachi Ltd ガスタービン翼
US5320483A (en) * 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
EP0698723A2 (de) * 1994-08-23 1996-02-28 General Electric Company Geschlossener Kühlkreislauf für Turbinenleitschaufel

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 017, no. 133 (M-1383), 19 March 1993 (1993-03-19) & JP 04 311604 A (TOSHIBA CORP), 4 November 1992 (1992-11-04) *
PATENT ABSTRACTS OF JAPAN vol. 017, no. 379 (M-1447), 16 July 1993 (1993-07-16) -& JP 05 065802 A (TOSHIBA CORP), 19 March 1993 (1993-03-19) *
PATENT ABSTRACTS OF JAPAN vol. 018, no. 360 (M-1634), 7 July 1994 (1994-07-07) -& JP 06 093801 A (HITACHI LTD), 5 April 1994 (1994-04-05) *
See also references of WO9850684A1 *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6783323B2 (en) * 2001-07-11 2004-08-31 Mitsubishi Heavy Industries, Ltd. Gas turbine stationary blade
US7168914B2 (en) 2001-07-11 2007-01-30 Mitsubishi Heavy Industries, Ltd. Gas turbine stationary blade
EP1571296A1 (de) * 2004-03-01 2005-09-07 Alstom Technology Ltd Gekühlte Strömungsmaschinenschaufel und Verfahren zur Kühlung
EP1788192A3 (de) * 2005-11-21 2008-11-12 General Electric Company Gasturbinenrotorschaufel mit gekühlter Plattformkante und Kühlverfahren für eine Plattformleitkante
EP2610436A3 (de) * 2011-12-30 2017-06-21 General Electric Company Kühlung der Plattform einer Turbinenrotorschaufel

Also Published As

Publication number Publication date
CA2261184C (en) 2002-07-09
JP3276305B2 (ja) 2002-04-22
JPH10306706A (ja) 1998-11-17
EP0911488A4 (de) 2000-11-29
DE69821312D1 (de) 2004-03-04
CA2261184A1 (en) 1998-11-12
EP0911488B1 (de) 2004-01-28
WO1998050684A1 (fr) 1998-11-12
DE69821312T2 (de) 2005-08-04

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