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WO1999036675A1 - Aube fixe de turbine a gaz - Google Patents

Aube fixe de turbine a gaz Download PDF

Info

Publication number
WO1999036675A1
WO1999036675A1 PCT/JP1998/000184 JP9800184W WO9936675A1 WO 1999036675 A1 WO1999036675 A1 WO 1999036675A1 JP 9800184 W JP9800184 W JP 9800184W WO 9936675 A1 WO9936675 A1 WO 9936675A1
Authority
WO
WIPO (PCT)
Prior art keywords
cooling
air
gas turbine
passage
steam
Prior art date
Application number
PCT/JP1998/000184
Other languages
English (en)
Japanese (ja)
Inventor
Kazuo Uematsu
Kiyoshi Suenaga
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
Priority to JP8190717A priority Critical patent/JPH1037704A/ja
Application filed by Mitsubishi Heavy Industries, Ltd. filed Critical Mitsubishi Heavy Industries, Ltd.
Priority to PCT/JP1998/000184 priority patent/WO1999036675A1/fr
Priority to CA002263576A priority patent/CA2263576C/fr
Priority to US09/230,751 priority patent/US6315518B1/en
Priority to DE19880989T priority patent/DE19880989C2/de
Publication of WO1999036675A1 publication Critical patent/WO1999036675A1/fr

Links

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
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • 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
    • F05D2260/221—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
    • 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 relates to a gas turbine stator vane capable of effectively performing cooling with a simple configuration.
  • the steam passage shall be closed to the outside and have a supply port and a recovery port.
  • cooling air is introduced into the inner shroud 35; cooling air is introduced from the inlet 40; Cooling air flows through 39 to cool the inner shroud 35, and the cooled air flows through the film cooling holes 38 provided in the inner shroud 35 into the main gas flow F to cool the film.
  • the current gas turbine steam-cooled vanes are in the above-mentioned situation and certainly have an advantage in terms of efficiency.However, closed long bent passages are complicated in structure and difficult to manufacture. In addition to this, if the wall thickness is increased to ease the pressure resistance, the whole blade becomes rigid and disadvantageous to thermal stress.
  • the present invention has been provided to solve the above problems. DISCLOSURE OF THE INVENTION
  • the stationary blade of the gas turbine of the present invention takes the following measures.
  • FIG. 1 is a cross-sectional view of an embodiment of the present invention
  • FIG. 2 is an A-A arrow diagram of FIG. 1
  • FIG. 3 is a cross-sectional view of a steam-cooled gas turbine vane of FIG.
  • FIG. 4 is a sectional view taken along the line BB in FIG. BEST MODE FOR CARRYING OUT THE INVENTION
  • the cooling steam flows from the cooling steam inlet 13 on the outer shroud 2 side into the inward cooling passage 8 provided in the wing 6, similarly to the conventional one shown in FIGS. After passing through the passage 8, it turns on the inner shaft 1 side, passes through the outward cooling passage 9 provided in the wing 6, and is collected at the cooling steam outlet 14.
  • the cooling steam is not supplied into the outer shroud, but the cooling steam is supplied to the inward cooling of the wing 6. It is supplied and discharged from the outward cooling passage 9 to the cooling steam outlet 14.
  • the inner shroud 1 and outer shroud 2 of the gas turbine vane are provided with cooling air inlet holes 3 for air cooling.On the other side of the cooling air inlet holes 3,-are many small-diameter passages.
  • a cooling air outlet hole 5 is provided through an accommodation plate 4 having holes.
  • the rear end 7 of the wing 6 which has a thin profile in terms of air performance corresponds to a pair of inward cooling passages 8 and outward cooling passages 9 for cooling the rear end 7 with air.
  • a large number of holes 11 are provided on the tail side of the air passage 1 (3), and as shown by the arrow, the cooling air flowing through the air passage 1 G flows into the main gas flow F discharged from the hole 1.
  • a hole 12 is also formed in the air shroud 1 side of the air passage 10 in the blade height direction, and the hole 12 is a part of the cooling air flowing through the air passage 10.
  • portions other than the rear end portion 7 of the wing portion 6 are connected to the inward cooling passage 8 and the outside cooling passage 8.
  • the inner shroud 1 and the outer shroud 2 are cooled by the cooling steam flowing through the cooling passage 9.
  • the inner shroud 1 and the outer shroud 2 flow through the cooling air inlet hole 3 and flow out of the cooling air outlet hole 5.
  • Cooling which can simplify the structure and locally uncooled
  • the cooling air supplied into the inner shroud 1 and the outer shroud 2 flows through the cooling air outlet hole 5 from the cooling air outlet hole 5 to the blades.
  • the film is discharged to the surface side of the part 6 to cool the surface of the wing part 6 by film, so that the cooling air can be used effectively. Since the air is flowed through the air passage 10, it is lined up, which is advantageous in terms of strength as compared with the case where high-pressure steam is used.
  • the cross-sectional area of the air passage 10 is increased, and the wing S
  • the thickness of the end 7 can be reduced, and effective cooling can be performed, and Binfin cooling can be performed.
  • the cooling air that has cooled the rear end 7 of the wing 6 is discharged from a number of holes 11 provided on the tail side of the rear end 7 of the wing 6 and merges with the main gas flow F. A part of the cooling air is discharged inward from the hole 12 on the inner shroud side of the air passage 10 to become the inner seal air of the combustion gas passage, and the inner seal air can be easily secured.
  • the vane of the gas turbine according to the present invention the complexity of the structure, which has been a problem of the conventional steam-cooled vane, has been reduced, and a part of the vane has been reduced. This can be solved by using air cooling, and the sealer inside the combustion gas passage can be easily secured. In addition, it is advantageous in terms of strength, and it is not unreasonable for ripening stress. Therefore, the reliability of the gas turbine can be further improved.

Landscapes

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

Abstract

L'invention concerne une aube fixe de turbine à gaz, de construction simple, capable d'assurer un refroidissement efficace dans un état où de l'air de refroidissement sous faible pression atténue une force de résistance à la pression. Un anneau intérieur (1) et un anneau extérieur (3) sont refroidis par de l'air de refroidissement, qui traverse un plateau de contact, et une extrémité arrière de partie d'aube (6) à configuration mince est refroidie par de l'air de refroidissement, lequel passe par un conduit d'air (10). Une partie de cet air est évacuée, en guise d'air isolant pour un conduit de gaz de combustion, depuis un orifice (12) placé sur un côté de l'anneau intérieur (1).
PCT/JP1998/000184 1996-07-19 1998-01-20 Aube fixe de turbine a gaz WO1999036675A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
JP8190717A JPH1037704A (ja) 1996-07-19 1996-07-19 ガスタービンの静翼
PCT/JP1998/000184 WO1999036675A1 (fr) 1996-07-19 1998-01-20 Aube fixe de turbine a gaz
CA002263576A CA2263576C (fr) 1998-01-20 1998-01-20 Aube fixe de turbine a gaz
US09/230,751 US6315518B1 (en) 1998-01-20 1998-01-20 Stationary blade of gas turbine
DE19880989T DE19880989C2 (de) 1998-01-20 1998-01-20 Stationäre Schaufel einer Gasturbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP8190717A JPH1037704A (ja) 1996-07-19 1996-07-19 ガスタービンの静翼
PCT/JP1998/000184 WO1999036675A1 (fr) 1996-07-19 1998-01-20 Aube fixe de turbine a gaz

Publications (1)

Publication Number Publication Date
WO1999036675A1 true WO1999036675A1 (fr) 1999-07-22

Family

ID=26439120

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP1998/000184 WO1999036675A1 (fr) 1996-07-19 1998-01-20 Aube fixe de turbine a gaz

Country Status (2)

Country Link
JP (1) JPH1037704A (fr)
WO (1) WO1999036675A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6647624B2 (en) 2001-07-05 2003-11-18 Alstom (Switzerland) Ltd Method of fitting an impingement plate
EP1526251A1 (fr) * 2003-10-22 2005-04-27 General Electric Company Configuration de refroidissement pour une aube de turbine
US7052233B2 (en) 2001-07-13 2006-05-30 Alstom Switzerland Ltd Base material with cooling air hole
DE10217484B4 (de) 2001-11-02 2018-05-17 Ansaldo Energia Ip Uk Limited Leitschaufel einer thermischen Turbomaschine
CN112112688A (zh) * 2019-06-21 2020-12-22 斗山重工业建设有限公司 透平静叶片、包含它的透平及燃气轮机
CN113266436A (zh) * 2021-05-14 2021-08-17 西安交通大学 用于燃气轮机静叶内部冷却的通道结构及燃气轮机静叶

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH1037704A (ja) * 1996-07-19 1998-02-10 Mitsubishi Heavy Ind Ltd ガスタービンの静翼
CA2263576C (fr) 1998-01-20 2003-08-05 Mitsubishi Heavy Industries, Ltd. Aube fixe de turbine a gaz
JP3494879B2 (ja) * 1998-03-25 2004-02-09 株式会社日立製作所 ガスタービン及びガスタービンの静翼
US6406254B1 (en) * 1999-05-10 2002-06-18 General Electric Company Cooling circuit for steam and air-cooled turbine nozzle stage
US6517312B1 (en) * 2000-03-23 2003-02-11 General Electric Company Turbine stator vane segment having internal cooling circuits
US6887039B2 (en) * 2002-07-10 2005-05-03 Mitsubishi Heavy Industries, Ltd. Stationary blade in gas turbine and gas turbine comprising the same
JP2009013837A (ja) * 2007-07-03 2009-01-22 Hitachi Ltd ガスタービン設備

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH02241902A (ja) * 1989-03-13 1990-09-26 Toshiba Corp タービンの冷却翼および複合発電プラント
JPH0681675A (ja) * 1992-09-03 1994-03-22 Hitachi Ltd ガスタービン及びガスタービンの段落装置
JPH08165902A (ja) * 1994-10-12 1996-06-25 Hitachi Ltd セラミック静翼
JPH09189203A (ja) * 1996-01-08 1997-07-22 Mitsubishi Heavy Ind Ltd ガスタービン静翼
JPH09264103A (ja) * 1996-03-28 1997-10-07 Mitsubishi Heavy Ind Ltd ガスタービン静翼
JPH1037704A (ja) * 1996-07-19 1998-02-10 Mitsubishi Heavy Ind Ltd ガスタービンの静翼

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH02241902A (ja) * 1989-03-13 1990-09-26 Toshiba Corp タービンの冷却翼および複合発電プラント
JPH0681675A (ja) * 1992-09-03 1994-03-22 Hitachi Ltd ガスタービン及びガスタービンの段落装置
JPH08165902A (ja) * 1994-10-12 1996-06-25 Hitachi Ltd セラミック静翼
JPH09189203A (ja) * 1996-01-08 1997-07-22 Mitsubishi Heavy Ind Ltd ガスタービン静翼
JPH09264103A (ja) * 1996-03-28 1997-10-07 Mitsubishi Heavy Ind Ltd ガスタービン静翼
JPH1037704A (ja) * 1996-07-19 1998-02-10 Mitsubishi Heavy Ind Ltd ガスタービンの静翼

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6647624B2 (en) 2001-07-05 2003-11-18 Alstom (Switzerland) Ltd Method of fitting an impingement plate
US7052233B2 (en) 2001-07-13 2006-05-30 Alstom Switzerland Ltd Base material with cooling air hole
DE10217484B4 (de) 2001-11-02 2018-05-17 Ansaldo Energia Ip Uk Limited Leitschaufel einer thermischen Turbomaschine
EP1526251A1 (fr) * 2003-10-22 2005-04-27 General Electric Company Configuration de refroidissement pour une aube de turbine
US6929445B2 (en) 2003-10-22 2005-08-16 General Electric Company Split flow turbine nozzle
CN112112688A (zh) * 2019-06-21 2020-12-22 斗山重工业建设有限公司 透平静叶片、包含它的透平及燃气轮机
CN112112688B (zh) * 2019-06-21 2023-02-17 斗山重工业建设有限公司 透平静叶片、包含它的透平及燃气轮机
CN113266436A (zh) * 2021-05-14 2021-08-17 西安交通大学 用于燃气轮机静叶内部冷却的通道结构及燃气轮机静叶

Also Published As

Publication number Publication date
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