WO1998050685A1 - Pale stationnaire servant au refroidissement d'une turbine a gaz - Google Patents
Pale stationnaire servant au refroidissement d'une turbine a gaz Download PDFInfo
- Publication number
- WO1998050685A1 WO1998050685A1 PCT/JP1998/001959 JP9801959W WO9850685A1 WO 1998050685 A1 WO1998050685 A1 WO 1998050685A1 JP 9801959 W JP9801959 W JP 9801959W WO 9850685 A1 WO9850685 A1 WO 9850685A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- steam
- cooling
- air
- shroud
- gas turbine
- Prior art date
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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a gas turbine cooling vane, and more particularly to a gas turbine cooling vane of a blade cooling type using both steam cooling and air cooling.
- the cooling of gas turbine vanes is air cooling, which consumes a large amount of cooling air. For this reason, a large amount of cooling air was sent to the blades, and the amount of cooling air leaked was large, forcing the performance of the gas turbine to deteriorate.
- a conventional typical air cooling method for a gas turbine stationary blade will be described.
- FIG. 5 shows an example of the appearance of a gas turbine stationary blade
- FIG. 6 is a cross-sectional view of the blade.
- 30 is the entire stationary blade
- 31 is the outer shroud
- 32 is the inner shroud
- 3 3, 3 4, 3 5 are inserts inside the stator vane and are divided into three sections
- 36 is a fin on the trailing edge.
- the outer shroud, inner shroud, insert and trailing edge fins Make up the wings.
- Each of the inserts 33, 34, 35 is supplied with high-pressure cooling air 38 from the outer shroud 31 side, and a number of cooling air holes 3 provided in the inserts 33, 34, 35 are provided. From 3a, 34a, and 35a, high-pressure cooling air is blown toward the wing to cool the inner surface of the wing. After that, the cooling air is blown out of the wing from the cooling air holes 37a, 37b, 37c, and 37d provided on the wing surface, and each of the wings has a head at the leading edge. Cooling, film cooling at the back and abdomen of the wings, and pin fin cooling at the trailing edge fins 36 are performed.
- FIG. 7 is a diagram showing another cooling method in a conventional gas turbine stationary blade
- FIG. 8 is a sectional view of the blade.
- 40 indicates the entire stator blade
- 41 indicates the outer shroud
- 42 indicates the inner shroud.
- air passages 4 3 A, 4 3 B, 43C, 43D, and 43E communicate with each other at the top and bottom to form a sa-pentine cooling passage.
- Numeral 45 denotes a fin on the trailing edge, which is provided with a number of air cooling holes 44 from which cooling air from the passage 43E blows.
- Reference numeral 46 denotes a large number of turbulences provided inside the air passages 43A to 43E for improving heat transfer.
- the cooling air 47 is supplied from the upper part of the air passage 43A located on the leading edge side of the outer shroud 41, flows downward, enters the air passage 43B, flows above the 43B, and then It enters 43C from the top, flows similarly to 43D and 43E, and cools the wing in each passage.
- the cooled air flows out of the cooling air hole 44 of the trailing edge fin 45, and the rest flows out of the wing through the lower part of the air passage 43E.
- cooling a stationary blade in a conventional gas turbine requires a large amount of cooling air and requires a large amount of power for the compressor and cooler. is the current situation.
- a main object of the present invention is to cool the stationary blades of the gas turbine by air cooling as in the past, and to introduce steam.
- To cool the blades and shroud greatly reduce the amount of cooling air used compared to conventional ones, reduce the load on the compressor and cooler, improve the performance of the gas turbine, and improve the efficiency of the shroud.
- An object of the present invention is to provide a cooling vane for a gas turbine that can be cooled by steam.
- Another object of the present invention is to use a combination of air cooling and steam cooling, use relatively high pressure cooling air for details that are difficult to pass steam, and use steam for the main part where steam is easy to pass. It is to provide gas turbine cooling vanes that cool by passing through and increase the cooling efficiency as a whole.
- Still another object of the present invention is to provide a gas turbine-cooled vane that is devised so as to collect steam and return it to a steam supply source without leaking to the outside of the blade when steam cooling as described above is employed. That is.
- Still another object of the present invention is to improve the steam inflow and outflow paths to improve the cooling efficiency by film cooling the trailing edge of the outer shroud, and installing the inbinge plate in the outer and inner shrouds. Therefore, the present invention provides the following means (1) and (7), respectively, in order to solve the above-mentioned problems. Summary of the Invention
- a gas turbine cooling vane has an outer shroud, an inner shroud, a blade disposed between the outer and inner shrouds, and an air cooling means for cooling the blade. Further, a steam cooling means for cooling the outer shroud, the inner shroud and the inside of the blade is provided, and steam cooling and air cooling by the steam cooling means and the air cooling means are used in combination.
- the outer shroud, the inner shroud and the blades are used not only for air cooling but also for introducing steam, so that the amount of air conventionally consumed in large amounts is reduced, and the compressor and The capacity of the cooler can also be reduced.
- a combined cycle facility combining a gas turbine and a steam turbine, By extracting part of the steam from the steam turbine, steam for cooling the stationary blades can be easily obtained, the cooling air can be greatly reduced, and the performance of the gas turbine can be improved. Furthermore, since the steam flows into the shroud for cooling, the cooling performance is improved.
- the air cooling means is applied to details that are difficult to pass the cooling steam, and the steam cooling means is provided at a main part where the cooling steam is easy to pass. It is characterized by being applied.
- the steam cooling means is a steam passage
- the air cooling means is an air passage
- the steam passage is an outer and inner shroud.
- the air passage is provided at a central portion where the wing is located and inside the wing, and the air passage is provided at a peripheral portion of the outer and inner shrouds and at a trailing edge of the wing. I do.
- each means is a passage
- the outer and inner shrouds and the blades can be efficiently cooled by cooling steam and cooling air.
- the center of the outer and inner shrouds, which are the main parts of the vane, and the leading edge of the blade are steam-cooled. Uses air cooling with a relatively high pressure difference, so that effective cooling can be achieved as a whole.
- the steam is introduced from the outer shroud, cools the outer and inner shrouds, and the inside of the blade. Effective use of steam and wings The effect of drain and the like due to the leakage of steam to the outside can be eliminated.
- the inside of the outer shroud is divided into a steam inflow side and a steam outflow side, and the steam supply side and the recovery side are simplified, and cooling is performed efficiently.
- FIG. 1 is a perspective view of a gas turbine cooling vane according to one embodiment of the present invention.
- FIG. 2 is a cross-sectional view of the cooling vane shown in FIG.
- FIG. 3 is a plan view of the outer shaft of the gas turbine cooling vane according to the embodiment of the present invention.
- FIG. 4 is a sectional view taken along line AA of FIG.
- FIG. 5 is a perspective view of a conventional cooling vane.
- FIG. 6 is a cross-sectional view of the conventional cooling vane shown in FIG.
- FIG. 7 is a longitudinal sectional view of another conventional cooling vane.
- FIG. 8 is a sectional view of the conventional cooling vane shown in FIG. Description of the preferred embodiment
- FIG. 1 is a perspective view of a gas turbine cooling vane according to an embodiment of the present invention
- FIG. 2 is a cross-sectional view of the vane.
- 1 is an outer shroud, the upper side of which is closed by steam lids 3 and 4.
- the steam lid 4 is provided with an inlet end of the seal air supply tube 2, and the tube 2 is provided so as to penetrate the upper and lower blades.
- Reference numeral 5 denotes a steam supply port provided in the steam cover 3 for guiding steam to a space below the steam covers 3 and 4.
- Reference numeral 6 denotes a cooling air supply port for supplying cooling air around the lower portion of the outer shroud 1.
- Reference numeral 7 is also a cooling air supply port for sending cooling air to the trailing edge of the wing.
- Reference numeral 8 denotes an impingement ⁇ , which is provided in the middle of the inner space of the outer shroud 1.
- This inbinge plate has a large number of holes, and the steam introduced from the steam supply port 5 collides to be dispersed and uniform, and the steam is ejected to the lower portion of the large number of holes to cool the outer shroud in the inbinge. Things.
- Reference numeral 9 denotes a cooling air passage. The cooling air is introduced into the outer periphery of the outer shroud 1, passes through the periphery of the shroud, and is discharged from the trailing edge side of the blade as shown by a dotted arrow.
- 10 A, 1 OB, 10 C, 10 D, and 10 E are steam passages for cooling inside the blade, and steam S is introduced from above the passage 1 OA at the leading edge.
- passage 10 The lower part of A communicates with passage 10B, the upper part of this passage 10B communicates with the upper part of passage 10C, and the lower part also communicates with passage 10D, and the lower part of passage 10D
- the upper part communicates with the steam outlets 12 to form a sa-pentine cooling system.
- Numeral 11 denotes a turbi-ure that is provided on the inner wall of each of the passages 10A to 10D to disturb the flowing steam and enhance heat transfer.
- an orthogonal table is arranged perpendicular to the cooling steam flow, and an oblique table is arranged behind it.
- 21 is an inner shroud
- 22 and 23 are steam lids at the lower part
- 24 is a steam reservoir at the upper part of the steam lid 22.
- Reference numeral 25 denotes an ininge board, which has a number of holes and is provided in the middle of the inner space of the inner shroud 21.
- the impingement plate 25 causes a part of the steam flowing into the steam reservoir 24 from the passage 10 A to be ejected from the steam reservoir 24 toward the inner shroud 21 through the many holes of the impingement ⁇ 25,
- the inner shroud 21 is in-binge-cooled.
- sealing air 13 is introduced from the seal air supply tube 2 and flows into the lower portion of the inner shroud 21 to be fed to the cavity (not shown). It guides the interior of the cavity to high pressure and seals against high-temperature gas from the external combustion gas passage.
- the cooling steam flows into the outer shroud 1 from the steam supply port 5 and collides with the inbinge plate 8 as shown by the thick black lines in Figs. 1 and 2, and the shroud 1 blades It flows into the lower part and cools the lower part uniformly. Thereafter, the cooling steam enters the cooling steam passage 1 OA at the leading edge of the wing, cools the leading edge and flows downward into the next passage 10 B, where the steam Part of the air enters the steam pool 24 of the lower inner shroud 21 and is jetted out of the many holes in the inbinge plate 25 toward the inner shroud 21 to cool the lower part of the inner shroud 21 uniformly. Then, it is recovered from the steam outlet 12 together with the steam in the passage 10D.
- the orthogonal and oblique turbulence in the passageway 10A is effective for cooling the leading edge of the wing.
- the steam entering the passage 10B cools this part in the process of flowing upward, enters the next passage 10C from the upper part, similarly flows to the passage 10D, and is located above the passage 10D. From the steam outlet 12 to be installed, it flows into a steam recovery passage (not shown) and is collected. This The steam cools the inside of the stator vane and the portions of the outer shroud 1 and the inner shroud 21 where the blades are located, and the steam is collected and returned to the steam supply source.
- cooling air is introduced into the outer shroud 1 via an air passage (not shown), passes through an air passage provided on the outer periphery of the outer shroud 1, and In FIG. 1, the air flows as shown by the dotted arrows to cool the periphery of the outer shroud 1, and is discharged through the air passage 9 to the side of the outer shroud 1 opposite to the cooling air supply port 6.
- the main part of the outer shroud 1 where the blades are located is cooled with steam, and cooling air is flowed around the periphery where steam is difficult to pass, and the details around the outer shroud 1 are reduced by the pressure difference of the high-pressure air. It cools down.
- Cooling air is also introduced from the cooling air supply port 26 of the inner shroud 21, and similarly flows around the inner shroud 21 as indicated by the dotted arrow, and cools the peripheral part of the inner shroud 21. Then, it is discharged outside from the rear cooling air outlet 27.
- the lower surface where the wings are located is cooled by steam, and the surrounding area where steam is difficult to pass is cooled by flowing cooling air in the same manner as the outer shroud 1.
- cooling air is guided to the passage 10E on the trailing edge of the wing, flows downward from the upper portion, and is blown out from the hole 60 on the trailing edge to cool the fin on the trailing edge to cool.
- the remaining air exits to the lower part of the inner shroud 21. In this way, cooling air should be applied to the narrow trailing edge of the passageway and the area where steam is difficult to pass through.
- FIG. 3 is a plan view of the outer shroud 1 described above.
- the cooling air 50 flowing from the cooling air supply port 6 shown in FIG. 1 passes through air passages 6 a and 6 b at both ends of the outer shroud, respectively. It cools both ends of the outer shroud and flows out from the air passage 9 (in FIG. 3, one at each end, but multiple ones at each end may be provided), which becomes the film cooling hole on the trailing edge side. The film is cooled.
- the cooling air supplied from the cooling air supply port 7 shown in FIG. 1 enters the slit 29, from which it enters the passage 10E at the trailing edge. Flows into In addition, the steam is supplied from the steam supply port 5 as described above, flows into the lower portion of the steam lids 3 and 4, cools the inner surface of the outer shroud 1, and is collected.
- FIG. 4 is a cross-sectional view taken along the line A-A in FIG. 3, and has steam chambers 52 a and 52 b partitioned by the steam lids 3 and 4 and the rib 51 as described above.
- the steam flows from the steam chamber 52a, and flows into the steam chamber 52b on the recovery side through the inside of the blade.
- the steam entering the steam chambers 52 a and 52 b collides with the inbinge plate 8 and spills out from a number of holes provided in the inbinge plate 8 to uniformly cool the inner surface of the outer shroud. it can.
- the cooling air enters the trailing edge passage 10E from the slit 29 and partly flows out from the air passage 9 to cool the film.
- a serpentine cooling system composed of passages 10A to 10D is formed inside the vane through steam, and a The provision of evening 11 enhances the efficiency of steam cooling.
- the in-binge plates 8, 25 are also provided in the main part where the outer shroud 1 and inner shroud 21 wings are located, and the in-binge cooling by steam is performed. I do.
- Cooling air is passed through the periphery of the outer shroud 1 and inner shroud 21 where steam is difficult to pass, and the passage 10E on the trailing edge fin side, and the details are cooled by the pressure difference of high pressure air. It uses steam cooling and air cooling together. As a result, compared to the conventional air-cooling only method, the amount of cooling air is greatly reduced and the power of the compressor and cooler is also reduced, thereby improving the performance of the gas turbine.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/202,690 US6142730A (en) | 1997-05-01 | 1998-04-28 | Gas turbine cooling stationary blade |
DE69825232T DE69825232T2 (de) | 1997-05-01 | 1998-04-28 | Kühlung einer statorschaufel bei einer gasturbine |
CA002260230A CA2260230C (en) | 1997-05-01 | 1998-04-28 | Cooled stationary blade of a gas turbine |
EP98917727A EP0911489B1 (en) | 1997-05-01 | 1998-04-28 | Gas turbine cooling stationary blade |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP9/113842 | 1997-05-01 | ||
JP11384297A JP3316415B2 (ja) | 1997-05-01 | 1997-05-01 | ガスタービン冷却静翼 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1998050685A1 true WO1998050685A1 (fr) | 1998-11-12 |
Family
ID=14622428
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP1998/001959 WO1998050685A1 (fr) | 1997-05-01 | 1998-04-28 | Pale stationnaire servant au refroidissement d'une turbine a gaz |
Country Status (6)
Country | Link |
---|---|
US (1) | US6142730A (ja) |
EP (1) | EP0911489B1 (ja) |
JP (1) | JP3316415B2 (ja) |
CA (1) | CA2260230C (ja) |
DE (1) | DE69825232T2 (ja) |
WO (1) | WO1998050685A1 (ja) |
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JP2971386B2 (ja) * | 1996-01-08 | 1999-11-02 | 三菱重工業株式会社 | ガスタービン静翼 |
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JP3495554B2 (ja) * | 1997-04-24 | 2004-02-09 | 三菱重工業株式会社 | ガスタービン静翼の冷却シュラウド |
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1997
- 1997-05-01 JP JP11384297A patent/JP3316415B2/ja not_active Expired - Fee Related
-
1998
- 1998-04-28 DE DE69825232T patent/DE69825232T2/de not_active Expired - Lifetime
- 1998-04-28 WO PCT/JP1998/001959 patent/WO1998050685A1/ja active IP Right Grant
- 1998-04-28 CA CA002260230A patent/CA2260230C/en not_active Expired - Lifetime
- 1998-04-28 EP EP98917727A patent/EP0911489B1/en not_active Expired - Lifetime
- 1998-04-28 US US09/202,690 patent/US6142730A/en not_active Expired - Lifetime
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JPH03115702A (ja) * | 1989-09-27 | 1991-05-16 | Hitachi Ltd | セラミック静翼 |
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 |
JPH06257405A (ja) * | 1992-12-30 | 1994-09-13 | General Electric Co <Ge> | タービン |
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Non-Patent Citations (1)
Title |
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See also references of EP0911489A4 * |
Also Published As
Publication number | Publication date |
---|---|
CA2260230C (en) | 2002-07-09 |
EP0911489A1 (en) | 1999-04-28 |
EP0911489A4 (en) | 2000-11-29 |
US6142730A (en) | 2000-11-07 |
CA2260230A1 (en) | 1998-11-12 |
DE69825232T2 (de) | 2005-08-04 |
EP0911489B1 (en) | 2004-07-28 |
JPH10306705A (ja) | 1998-11-17 |
JP3316415B2 (ja) | 2002-08-19 |
DE69825232D1 (de) | 2004-09-02 |
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