EP0911488B1 - Gas turbine cooled stationary blade - Google Patents
Gas turbine cooled stationary blade Download PDFInfo
- Publication number
- EP0911488B1 EP0911488B1 EP98917726A EP98917726A EP0911488B1 EP 0911488 B1 EP0911488 B1 EP 0911488B1 EP 98917726 A EP98917726 A EP 98917726A EP 98917726 A EP98917726 A EP 98917726A EP 0911488 B1 EP0911488 B1 EP 0911488B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- steam
- cooling
- stationary blade
- inner shroud
- passage
- 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.)
- Expired - Lifetime
Links
Images
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 trailing edge of the blade.
- Numeral 44 denotes air blowout holes at the trailing 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 trailing 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 leading 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 trailing 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.
- US 5,320,483 describes a cooled stationary blade assembly for a gas turbine. Steam is supplied from steam passages into a chamber in the outer side wall. After passing through a nozzle blade, the steam enters into the vanes which are subdivided into a plurality of individual compartments. The steam flows through a first cooling steam supply passage, a second return steam passage, a third leading edge cooling steam passage and a fourth steam passage. Moreover, there is an air passage. The steam passages lie in communication with a cooling channel disposed within the inner side wall. This cooling channel collects the steam and directs it to the downstream flow channel through the vane.
- EP-A-0 698 723 describes a cooled stationary blade assembly for a gas turbine comprising an inner shroud, an outer shroud and a stationary blade provided between the outer shroud and the inner shroud with a leading edge and a trailing edge.
- There is an air-cooling system which serves both to cool the inner shroud and the vanes.
- In the inner shroud there are inner chambers which are interconnected by openings with the inner compartments of the vanes. These compartments serve for an impingement cooling of the inner shroud.
- the stator vane has a plurality of discrete cavities between the leading and trailing edges and extending lengthwise for flowing a cooling medium.
- the cooling medium air serves to cool both the stator vane and the inner shroud. It is also mentioned to use steam as a cooling medium.
- JP-0-A-05065802 describes a steam cooling system for the stationary blade of a turbine.
- a steam supplying cavity which is connected to the cooling passages for steam through the vane.
- a cooling duct formed in the inner shroud of the stationary blade assembly.
- JP-A-06311604 refers to a blade assembly with a hollow vane which is subdivided into individual compartments by means of partition walls.
- the compartments are communicating with each other through a communicating passage in the inner shroud.
- the cooling steam is first guided to the center compartment of the vane and then, guided to those compartments in the leading edge part and the trailing edge compartment of the vane.
- JP-A-06093801 describes a vane body having a hollow structure, the inside of which is sectioned into a vane internal cavities by partition walls.
- An insert having a plurality of jet holes is located in the cavities of the vane body. Cooling medium fed into an internal cooling medium passage is jetted onto the inner surface of the vane body through the jet ports at a high speed.
- 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.
- a cooled stationary blade assembly for a gas turbine is characterized by comprising an outer shroud, an inner shroud, a stationary blade provided between the outer and inner shrouds with a leading edge and a trailing edge, a first steam cooling means provided in an interior of the stationary blade for cooling steam, and a second steam cooling means provided in the inner shroud and communicated with the first steam cooling means in order to flow a portion of the cooling steam.
- the interior of the blade is cooled with the steam by the first and second steam cooling means, and at the same time, the inner shroud may also be cooled with steam, the conventional cooling air is dispensed with, the power consumption of the compressor or the cooler may be conserved, and the cooling air is not discharged into the combustion gas passage. As a result, the temperature of the combustion gas is not towered and a reduction in turbine efficiency is prevented.
- the first steam cooling means and the second steam cooling means are communicated with each other at the leading edge and at the trailing edge of the stationary blade, a portion of the cooling steam is introduced from the first steam cooling means to the second steam cooling means at the leading edge of the stationary blade, and the cooling steam that passes through the second steam cooling means is returned to the first steam cooling means at the trailing edge of the stationary blade.
- the cooled stationary blade assembly for a gas turbine is preferably characterized in that the first steam cooling means is first steam passages, the cooling steam is introduced into the steam passages o n the leading edge of the stationary blade through the outer shroud, and the cooling steam flows out of the steam passages on the trailing edge through the outer shroud.
- the cooling steam flows through the steam passage, it is possible to effectively cool the blade.
- the cooling steam that has been introduced into the blade is used to cool the blade and the inner shroud so that its temperature increases.
- the steam is recovered through the outer shroud and returned to the steam feed source. The steam is effectively utilized so the efficiency of the turbine is increased.
- the cooled stationary blade assembly for a gas turbine is characterized in that the second steam cooling means comprises channels arranged in both side end portions of the inner shroud.
- the cooling steam flows through the periphery of the inner shroud to effectively cool the inner shroud.
- the cooled stationary blade assembly for a gas turbine is preferably characterized in that the second steam cooling means of the inner shroud is composed of a groove provided along a peripheral side surface of the inner shroud and a side plate for covering the groove.
- the second steam cooling means is thus constructed so that its formation at the end portion of the inner shroud is facilitated.
- Fig. 1 is a schematic view 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 leading 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 trailing 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 leading 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 trailing 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 leading 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 trailing edge side of the blade.
- the cooling steam is introduced from the steam passage 33A on the leading 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 side end portions of the inner shroud 31 and flow to the trailing 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 trailing 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 leading 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 trailing edge side of the blade from the steam passage 33F at the trailing 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.
Description
Claims (4)
- A cooled stationary blade assembly for a gas turbine, comprising an outer shroud, an inner shroud (31), a stationary blade provided between said outer shroud and said inner shroud (31) with a leading edge and a trailing edge, first steam cooling means (33A to 33F) provided in an interior of said stationary blade for cooling steam (39), and a second steam cooling means (20) provided in said inner shroud and communicated with said first steam cooling means in order to flow a portion of said cooling steam;
characterized in that
said first steam cooling means (33A to 33F) and said second steam cooling means (20) are communicated with each other at said leading edge and at said trailing edge of said stationary blade;
the portion of the cooling steam (39) being introduced from said first steam cooling means to said second steam cooling means at said leading edge of said stationary blade;
said cooling steam that passes through said second steam cooling means being returned to said first steam cooling means at said trailing edge of said stationary blade; and
the second steam cooling means comprising channels leading the steam through both shroud side end portions of the inner shroud. - The cooled stationary blade assembly for a gas turbine according to claim 1, wherein said first steam cooling means comprises first steam passages (33A to 33F), said cooling steam is introduced into said steam passages at said leading edge of said stationary blade (30) through said outer shroud, and said cooling steam flows out of said steam passages at said trailing edge through said outer shroud.
- The cooled stationary blade assembly for a gas turbine according to claim 1 or 2, wherein said second steam cooling means comprises a second steam passage (20) and is arranged in the vicinity of shroud side end portions of said inner shroud (31).
- The cooled stationary blade assembly for a gas turbine according to claim 1, wherein said second steam cooling means (20) of said inner shroud (31) is composed of a groove provided along a peripheral side surface of said inner shroud and a side plate for covering said groove.
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP113845/97 | 1997-05-01 | ||
JP11384597A JP3276305B2 (en) | 1997-05-01 | 1997-05-01 | Gas turbine cooling vanes |
JP11384597 | 1997-05-01 | ||
PCT/JP1998/001958 WO1998050684A1 (en) | 1997-05-01 | 1998-04-28 | Gas turbine cooling stationary blade |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0911488A1 EP0911488A1 (en) | 1999-04-28 |
EP0911488A4 EP0911488A4 (en) | 2000-11-29 |
EP0911488B1 true EP0911488B1 (en) | 2004-01-28 |
Family
ID=14622507
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98917726A Expired - Lifetime EP0911488B1 (en) | 1997-05-01 | 1998-04-28 | Gas turbine cooled stationary blade |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP0911488B1 (en) |
JP (1) | JP3276305B2 (en) |
CA (1) | CA2261184C (en) |
DE (1) | DE69821312T2 (en) |
WO (1) | WO1998050684A1 (en) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4508482B2 (en) * | 2001-07-11 | 2010-07-21 | 三菱重工業株式会社 | Gas turbine stationary blade |
EP1571296A1 (en) * | 2004-03-01 | 2005-09-07 | Alstom Technology Ltd | Cooled blade of a turbomachine and method of cooling |
US7147439B2 (en) * | 2004-09-15 | 2006-12-12 | General Electric Company | Apparatus and methods for cooling turbine bucket platforms |
US7309212B2 (en) * | 2005-11-21 | 2007-12-18 | General Electric Company | Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge |
JP4931157B2 (en) * | 2006-02-14 | 2012-05-16 | 株式会社Ihi | Cooling structure |
JP4979983B2 (en) * | 2006-05-29 | 2012-07-18 | 三井造船株式会社 | Dust adhesion prevention device for furnace top pressure recovery turbine blade |
JP4801618B2 (en) * | 2007-03-30 | 2011-10-26 | 三菱重工業株式会社 | Gas turbine stationary blade and gas turbine provided with the same |
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 |
US8905714B2 (en) * | 2011-12-30 | 2014-12-09 | General Electric Company | Turbine rotor blade platform cooling |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH04311604A (en) * | 1991-04-11 | 1992-11-04 | Toshiba Corp | Turbine stationary blade |
JP3015531B2 (en) * | 1991-09-06 | 2000-03-06 | 株式会社東芝 | gas turbine |
JP2953842B2 (en) * | 1991-12-16 | 1999-09-27 | 東北電力株式会社 | Turbine vane |
JPH0693801A (en) * | 1992-09-17 | 1994-04-05 | Hitachi Ltd | Gas turbine |
US5320483A (en) * | 1992-12-30 | 1994-06-14 | General Electric Company | Steam and air cooling for stator stage of a turbine |
JP3188105B2 (en) * | 1994-07-11 | 2001-07-16 | 三菱重工業株式会社 | Gas turbine blades |
US5634766A (en) * | 1994-08-23 | 1997-06-03 | General Electric Co. | Turbine stator vane segments having combined air and steam cooling circuits |
-
1997
- 1997-05-01 JP JP11384597A patent/JP3276305B2/en not_active Expired - Fee Related
-
1998
- 1998-04-28 WO PCT/JP1998/001958 patent/WO1998050684A1/en active IP Right Grant
- 1998-04-28 DE DE69821312T patent/DE69821312T2/en not_active Expired - Lifetime
- 1998-04-28 EP EP98917726A patent/EP0911488B1/en not_active Expired - Lifetime
- 1998-04-28 CA CA002261184A patent/CA2261184C/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
CA2261184C (en) | 2002-07-09 |
EP0911488A1 (en) | 1999-04-28 |
JP3276305B2 (en) | 2002-04-22 |
JPH10306706A (en) | 1998-11-17 |
EP0911488A4 (en) | 2000-11-29 |
DE69821312D1 (en) | 2004-03-04 |
CA2261184A1 (en) | 1998-11-12 |
WO1998050684A1 (en) | 1998-11-12 |
DE69821312T2 (en) | 2005-08-04 |
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Inventor name: ISHIGURO, TATSUOC/O TAKASAGO RES. & DEVEL. CEN Inventor name: SUENAGA, KIYOSHIC/O TAKASAGO RES. & DEVEL. CEN Inventor name: AOKI, SUNAOC/O TAKASAGO MACHINERY WORKS Inventor name: TOMITA, YASUOKIC/O TAKASAGO MACHINERY WORKS |
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