WO1999036675A1 - Aube fixe de turbine a gaz - Google Patents
Aube fixe de turbine a gaz Download PDFInfo
- 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
Links
- 238000001816 cooling Methods 0.000 claims abstract description 60
- 239000007789 gas Substances 0.000 claims abstract description 25
- 239000000567 combustion gas Substances 0.000 claims abstract description 5
- 238000010276 construction Methods 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 230000004308 accommodation Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000005070 ripening Effects 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
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)
Description
Claims
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 (en) | 1998-01-20 | 1998-01-20 | Stationary blade of gas turbine |
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 (ja) |
WO (1) | WO1999036675A1 (ja) |
Cited By (6)
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 (en) * | 2003-10-22 | 2005-04-27 | General Electric Company | Turbine nozzle cooling configuration |
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)
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 (en) | 1998-01-20 | 2003-08-05 | Mitsubishi Heavy Industries, Ltd. | Stationary blade of gas turbine |
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)
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 |
-
1996
- 1996-07-19 JP JP8190717A patent/JPH1037704A/ja active Pending
-
1998
- 1998-01-20 WO PCT/JP1998/000184 patent/WO1999036675A1/ja active Application Filing
Patent Citations (6)
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)
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 (en) * | 2003-10-22 | 2005-04-27 | General Electric Company | Turbine nozzle cooling configuration |
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 |
---|---|
JPH1037704A (ja) | 1998-02-10 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP3316405B2 (ja) | ガスタービン冷却静翼 | |
JP3316415B2 (ja) | ガスタービン冷却静翼 | |
US7632062B2 (en) | Turbine rotor blades | |
JP4801513B2 (ja) | ターボ機械の可動な翼のための冷却回路 | |
JP4644465B2 (ja) | 分割流式タービンノズル | |
JP3978143B2 (ja) | 静翼の冷却構造及びガスタービン | |
CN101029581B (zh) | 用于冷却燃气涡轮机转子叶片的方法和设备 | |
JP5947524B2 (ja) | ターボ機械静翼、及びターボ機械静翼を冷却する方法 | |
JP3631500B2 (ja) | ガスタービン用の一体化蒸気/空気冷却装置及びガスタービン用の冷却装置を動作する方法 | |
JP3844324B2 (ja) | ガスタービンエンジンタービンブレード用スクイーラ及びガスタービンエンジンタービンブレード | |
US7497655B1 (en) | Turbine airfoil with near-wall impingement and vortex cooling | |
JP2971386B2 (ja) | ガスタービン静翼 | |
CN106907183B (zh) | 带有后缘冷却回路的涡轮翼型件 | |
JPH02233802A (ja) | 冷却式タービン羽根 | |
WO1999036675A1 (fr) | Aube fixe de turbine a gaz | |
US6758651B2 (en) | Gas turbine | |
EP2264283A2 (en) | A cooled component for a gas turbine engine | |
CA2231690A1 (en) | Cooled stationary blade for a gas turbine | |
WO2023171745A1 (ja) | ガスタービンの静翼の冷却方法および冷却構造 | |
JP2005146858A (ja) | ガスタービン | |
US6315518B1 (en) | Stationary blade of gas turbine | |
JPH11193701A (ja) | タービン翼 | |
EP3091182B1 (en) | Blade | |
JP4137508B2 (ja) | リフレッシュ用孔のメータリング板を備えるタービン翼形部 | |
JP2004084601A (ja) | 燃焼器およびガスタービン |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WWE | Wipo information: entry into national phase |
Ref document number: 09230751 Country of ref document: US |
|
ENP | Entry into the national phase |
Ref document number: 2263576 Country of ref document: CA |
|
AK | Designated states |
Kind code of ref document: A1 Designated state(s): CA DE US |
|
RET | De translation (de og part 6b) |
Ref document number: 19880989 Country of ref document: DE Date of ref document: 20000113 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 19880989 Country of ref document: DE |