WO1998055735A1 - Aube de turbine a gas - Google Patents
Aube de turbine a gas Download PDFInfo
- Publication number
- WO1998055735A1 WO1998055735A1 PCT/JP1998/002454 JP9802454W WO9855735A1 WO 1998055735 A1 WO1998055735 A1 WO 1998055735A1 JP 9802454 W JP9802454 W JP 9802454W WO 9855735 A1 WO9855735 A1 WO 9855735A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blade
- cooling
- steam
- gas turbine
- cooling medium
- 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
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- 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 blade provided with a steam cooling structure.
- the cooling heat of the gas turbine is recovered from the recovered steam by the steam turbine, thereby preventing a decrease in the efficiency of the entire plant and suppressing the amount of the cooling medium blown into the gas turbine.
- the efficiency of the bin can be improved.
- the heat transfer performance can be greatly improved without significantly changing the conventional cooling passage shape.
- FIG. 5a and 5b show a typical internal cooling structure of the moving blade in the conventional recovery type steam-cooled gas turbine described above.
- FIG. 5a shows a vertical section of the wing
- FIG. 5b shows a section taken along line 5B-5B in FIG. 5a.
- the cooling steam of the moving blade 1 is supplied from a cooling steam inlet 8 provided at the lower part of the blade on the side of the leading edge 5 of the blade, passes through a cooling passage 4 formed in a sagittal pentane shape in the moving blade 1, and becomes an arrow. After cooling the inside of the blade, it flows out of the blade through the cooling steam outlet 9 on the trailing edge 6 side of the blade, and is guided to a recovery system (not shown).
- a plurality of turbulence promoting fins 7 are provided on the inner surface of the cooling passage 4 to extend in a direction intersecting the flow of the cooling steam, so that the internal heat transfer is promoted.
- the pressure inside the cooling blade is kept 2 to 4 MPa higher than the gas pressure outside the blade surface. Therefore, an internal pressure exceeding the allowable limit of the strength of the thin-walled hollow blade is applied inside the blade, and the blade deforms (bulges) and swells, causing fluid separation of the working gas on the blade surface and degrading the performance of the blade. It will cause problems such as lowering, and it is required that the structure be at least able to withstand this.
- the present invention responds to such needs and ensures the strength of the blades, and fully enjoys the advantages of the steam cooling system, which aims to improve the thermal efficiency of the gas turbine, without impairing the advantages. It is an object of the present invention to provide a gas turbine blade that can be used.
- the present invention has been made to achieve this object, and forms a cooling medium flow path extending in the blade length direction inside the blade, and extends in the cooling medium flow path in the flow direction of the cooling medium to form a blade.
- An object of the present invention is to provide a gas bottle having a reinforcing rib connecting a back side and a ventral side.
- the reinforcing rib is provided inside the wing. Since it extends in the flow direction of the cooling medium in the cooling flow path formed to extend in the blade length direction, it does not obstruct the flow of the high-pressure steam as the cooling medium and does not change the flow state with or without the reinforcing ribs The desired cooling effect is achieved.
- the present invention provides a gas turbine single-blade blade wherein the cooling medium flow path is formed by partitioning the partition wall, and the reinforcing ribs are arranged at positions not blocking the left and right flow paths between adjacent partition walls. Is what you do.
- the width of the cooling medium flow path is narrowed by positioning the reinforcing ribs between adjacent partition walls forming the cooling medium flow path, preferably at the center so as not to block the flow path, thereby reducing the width of the cooling medium flow path. Due to the pressure difference between the pressure of the cooling steam flowing through the cooling medium flow path and the pressure of the main gas flowing outside the cooling medium flow path, the amount of bulging of the flow path expanding from the cooling steam side is reduced.
- the present invention also provides a gas turbine blade configured to have independent structures in which the left and right flow paths of the reinforcing rib form independent flow characteristics.
- each of the cooling medium flow paths partitioned on the left and right sides has the property of the cooling steam flowing through the flow path. It is configured in an independent form to conform to that, and achieves effective heat exchange and heat recovery.
- the present invention provides a gas turbine blade configured to supply and recover cooling steam supplied to and recovered from the cooling medium flow path from a supply inlet and a recovery outlet protruding forward and rearward of the blade root. I do.
- the supply inlet for introducing the cooling steam into the cooling medium flow path, and the cooling steam recovery outlet that has received the heat from the turbine blades after the cooling operation has finished projecting forward and backward from the blade root Since it is configured, it can be easily processed and worked, including the connection structure at this part, and the leakage of cooling steam, which causes a reduction in efficiency, can be appropriately prevented.
- the reinforcing ribs are provided only in the cooling medium flow path at the trailing end of the blade, and the other cooling medium flow paths are divided into a large number of short sections so as to have a circular cross section. I will provide a.
- the cooling medium flow path having a substantially circular cross section does not require reinforcing ribs, so it should be installed there.
- the reinforcing ribs are installed by selecting only the cooling medium flow path at the trailing edge of the blade, which is difficult to make the cross section close to a circular shape because the overall shape is narrow, and the reinforcing ribs are installed over the entire blade The cost of design and production is omitted, and the wings are obtained with sufficient strength.
- a section near the trailing edge of the blade is widened to make it easier for cooling steam to flow, and arranged near the trailing edge of the blade.
- the rib has a structure in which the tip end on the tip side is bent toward the corner of the wing to improve the flow of cooling steam at the corner and improve the cooling performance.
- FIGS. 1a and 1b show a steam-cooled gas turbine blade according to a first embodiment of the present invention, wherein FIG. 1a is a longitudinal sectional view, and FIG. 1b is 1B—1B of FIG. 1a. It is sectional drawing along the line.
- FIG. 2a and 2b show a steam-cooled gas turbine blade according to a second embodiment of the present invention, wherein FIG. 2a is a longitudinal sectional view, and FIG. 2b is 2B—2B in FIG. 2a. It is sectional drawing along the line.
- FIG. 3a and 3b show a steam-cooled gas turbine blade according to a third embodiment of the present invention, where FIG. 3a is a longitudinal sectional view, and FIG. 3b is 3B—3B in FIG. 3a. It is sectional drawing along the line.
- FIG. 4a and 4b show a steam-cooled gas turbine according to a fourth embodiment of the present invention.
- FIG. 4a is a longitudinal sectional view
- FIG. 4b is a view taken along line 4-4 in FIG. 4a.
- It is sectional drawing. 5a and 5b show a conventional steam-cooled gas turbine blade
- FIG. 5a is a longitudinal sectional view
- FIG. 5b is a sectional view taken along line 5B-5B in FIG. 5a. .
- FIGS. 1A and 1B A first embodiment of the present invention will be described with reference to FIGS. 1A and 1B.
- Fig. 1a shows a longitudinal section of a steam turbine blade for steam cooling
- Fig. 1b shows a section taken along line 1B-1B of Fig. 1a. Note that the same parts as those of the above-described conventional technique are denoted by the same reference numerals in the drawings, and redundant description will be omitted.
- the interior of the rotor blade 1 communicates in a serpentine shape, and extends from the blade root side to the blade tip 11 side, further from the blade tip 11 side to the blade root side, and the longitudinal direction of the rotor blade 1
- reinforcing blades 12 are provided which connect the blade abdominal side 2 and the blade back side 3 and extend in a substantially central portion of the cooling passage 4 in a longitudinal direction.
- each folded portion of the blade tip 1 1 side of the cooling passage 4 communicating with the serpentine shape, c present embodiment are disposed a short reinforcing ribs 1 3 bent along the curve of the wrapping as a steam Since the reinforcing ribs 12 and 13 are provided in the cooling passage 4, the pressure difference between the high-pressure steam for cooling flowing in the cooling passage 4 and the main gas 10 flowing outside the rotor blade 1 (usually 2 to 4 MPa) can provide strength sufficient to withstand the force acting on the bucket 1.
- the reinforcing ribs 1 and 2 are arranged along the direction in which the cooling passage 4 extends, so The reinforcement ribs 13 are bent along the turn-back curve of the cooling passage 4 without being disturbed by the cooling steam flow.
- the shape of the reinforcing ribs 12 and 13 used here is a shape with low hydrodynamic pressure loss, that is, the front and rear edges of the reinforcing ribs 12 and 13 are rounded, and the size is dynamic.
- the width should be strong enough to withstand the pulling from the flank side 2 and the wing back side 3 of the wing 1.
- the specific dimensions are determined by the scale of the target turbine.
- FIGS. 2A and 2B show a longitudinal sectional view of a steam turbine blade for steam cooling
- Fig. 2b shows a 2B-2B section of Fig. 2a.
- a cooling passage 4 which is bent in a sun-shaped manner by a U-shaped partition wall 14a and an I-shaped partition wall 14b arranged to be inserted in the center thereof. Reinforcing ribs 12 are arranged almost at the center between the partition walls 14a, 14b, etc., to ensure the strength of the blades hitting the cooling passage 4. Paying particular attention to the cooling passage 4 formed near the trailing edge 6 of the wing, the turbulent flow promoting fins (Tabileure) on both the left and right sides of the reinforcing ribs 12 arranged in the cooling passage 4 7 a and 7 b are different from the configuration related to the reinforcing ribs 12 in the other cooling passages 4.
- the other cooling passages 4 are arranged in such a manner that the reinforcing ribs 12 are arranged simply and straightly on the turbulent flow promoting fins 7 extending uniformly over the entire width of the cooling passage 4.
- the left and right sides of the reinforcing ribs 12 are arranged in a shape independent of each other.
- a turbulence promoting fin 7a on one side of the reinforcing rib 12 is provided.
- the turbulence-promoting fins 7b on the other side have different inclination directions from each other, and also have different numbers of arrangements (array mesh).
- a cooling steam inlet 8 is provided so as to protrude slightly forward on the leading edge side, and a cooling steam outlet 9 is provided slightly protruding rearward on the trailing edge side.
- the cooling steam outlet 9 are formed so as to protrude outward, so that the working environment for machining and machining in this area is ensured in favorable conditions, improving workability and reliably preventing steam leakage. can do.
- FIGS. 3A and 3B show a third embodiment of the present invention.
- Fig. 3a shows a longitudinal section of a steam turbine blade for steam cooling
- Fig. 3b shows a section taken along line 3B-3B in Fig. 3a.
- the reinforcing ribs 12 are provided only for those located at the rear end of the blade 1 in the cooling passage 4 bent in a serpentine shape.
- each cooling passage 4 bent in the shape of the pen when the cooling passage 4 bent in the shape of the pen is formed inside the wing 1, many partition walls 14 are used to finely partition the inside of the wing 1. (In contrast to a partition of about 4 sections, here, it is divided into 6 sections here.) However, each cooling passage 4 has an almost circular shape and is strong in strength.
- the partition wall 14 is not provided until the shape of the cooling passage 4 at this position approaches a circle, and the reinforcing rib 1
- the partition wall 14 is arranged in a short section from the leading edge side of the wing 1 to the center and up to just before the trailing edge, so that the strength is given by the substantially circular cooling passage 4, Designed to install reinforcing ribs 1 and 2 over the entire wing by selecting only the cooling flow path 4 at the trailing end of the wing, which is difficult to make the cross section close to a circular shape due to its overall shape being thin. However, the production cost was reduced, and wings with sufficient strength were obtained.
- a bypass hole 16 is provided below the partition wall 14 so that a part of the cooling steam flowing through the cooling passage 4 is bypassed without being bent in a serpentine shape, and is bypassed. It is devised to adjust the temperature balance and so on.
- FIG. 4a and 4b show a cross section of a steam-cooled gas turbine blade according to a fourth embodiment of the present invention, and FIG. 4a shows a cut in a radial direction of the gas turbine, that is, in a blade length direction of the blade.
- Fig. 4b shows a cross section taken along line 4B-4B of Fig. 4a.
- the rib 1 extending in the blade length direction of the moving blade 1 is formed in the cooling passage 4 formed on the blade trailing edge 6 side and supplied with the cooling steam from the cooling steam inlet 8 a on the hub side.
- 2 3 arranged to a and c are partitioned the cooling passage 4 into four flow paths, the interval between the flow passages divided by the respective ribs 1 2, is closest to the trailing edge 6
- the pitch is the widest as shown as pitch 17, the other flow path is narrower, and the flow path space is the largest at the rear of the blade ⁇ 6, so that cooling steam flows easily. Have been.
- the tip 12-1 of the wing tip 11 of the rib 12 placed closest to the wing trailing edge 6 is located at the position where the wing tip 11 and the wing trailing edge 6 intersect. It is bent toward the corner 18 so that the flow of the cooling steam can reach the corner 18 sufficiently and reliably.
- the cooling steam flows from the rotor side (not shown) to the rotor blade 1 via the cooling steam inlet 8b on the blade leading edge side and the cooling steam inlet 8a on the trailing edge side of the blade.
- the cooling steam is supplied, flows through the cooling passage 4 that is continuous with the cooling steam inlets 8a, 8b, returns at the wing tip 11 and returns to the hub side from the cooling steam outlets 9a, 9b.
- the cooling passage 4 provided on the blade trailing edge 6 side has a small blade thickness because it is the blade trailing edge 6, but the ribs 12 are arranged in the cooling passage 4 as described above, and the cooling passage is formed.
- the cooling steam supplied to this difficult-to-flow area also flows through the easy-to-flow section near the trailing edge 6 of the blade, ensuring the cooling effect of the internal passage near the trailing edge 6 of the blade. I can do it.
- the cooling passage 4 near the trailing edge 6 of the wing is bent toward the corner 18 of the wing, because the tip 12-1 of the wing tip 11 of the rib 12 defining the wing 12 is bent toward the corner 18 of the wing.
- a cooling steam flow 19 flowing along the ribs 12 and turning back at the same corner 18 is formed, and a dead water region where cooling steam is not supplied is not formed, and the wing trailing edge 6
- the convective cooling transmission rate can be increased over the entire area of the cooling passage 4.
- the cooling passage 4 near the trailing edge 6 of the wing is divided into four channels by arranging three ribs 12, but the number of ribs 12 arranged here and the number of sections
- the number of blades is not limited to this, and the number of blades can be appropriately changed according to the shape and scale of the wing 1.
- cooling passage 4 is described as the smallest serpentine passage that exits from the hub side and turns back at the blade tip 11 to reach the cooling steam outlets 9a and 9b, but the size and design of the rotor blade 1 are described. Needless to say, a large serpentine-in structure in which this folding is repeated a plurality of times can be made according to manufacturing requirements.
- the reinforcing ribs in the rotor blade internal cooling passage strength capable of withstanding the force generated by the pressure difference between the high-pressure steam in the blade and the gas outside the blade is obtained, and the safety and stability are improved. High wings could be obtained.
- the cooling steam flows through the internal passage almost in the same way as when there is no rib, achieving the desired effect without impairing the internal convection cooling performance I got the wings to do.
- the reinforcing ribs when arranging the reinforcing ribs in the cooling medium flow paths partitioned by the partition walls, the reinforcing ribs do not block the left and right flow paths between the adjacent partition walls. Placed in position.
- the width of the cooling medium flow path is narrowed by arranging reinforcing ribs, for example, at the center between adjacent partition walls forming the cooling medium flow path so as not to block the flow path.
- the left and right flow paths of the reinforcing rib provided in the cooling medium flow path formed in the gas turbine blade form independent flow characteristics from each other. It is configured.
- the reinforcing ribs are not simply arranged in the cooling medium flow path, and the cooling medium flow paths divided into right and left by arranging the reinforcing ribs are the cooling steam flowing on each side. Since it can be configured in an independent form according to the nature of the heat exchanger, effective heat exchange and heat recovery can be achieved.
- the cooling steam supplied to and recovered from the cooling medium channel formed in the gas turbine blade is supplied from a supply inlet and a recovery outlet projecting forward and rearward of the blade root. It is configured to be collected.
- this portion is formed so as to protrude forward and rearward of the blade root, so that the processing and work including the connection structure at this portion are performed. This facilitated and prevented the leakage of connected steam, which causes a reduction in efficiency, appropriately and reliably.
- the reinforcing rib provided in the cooling medium flow path formed inside the gas turbine blade is provided only in the cooling medium flow path at the rear end of the blade, and the other cooling medium is provided.
- the flow path is formed by dividing the flow path into a large number of short sections so that the cross section becomes almost circular.
- the cooling medium flow path having a substantially circular cross section has high strength and does not require reinforcing ribs. It was not installed there, and the reinforcing ribs were installed by selecting only the cooling medium flow path at the trailing edge of the blade, whose overall shape was narrow and it was difficult to make the cross section nearly circular. The design and production costs for installing the reinforcing ribs were eliminated, and the entire wing could be obtained with sufficient strength.
- a cooling passage of the trailing edge of the blade is divided into a plurality of sections by ribs extending in a blade length direction, and a section close to the trailing edge of the blade is provided.
- the tip of the tip located near the trailing edge of the blade is bent toward the corner of the blade to form the gas turbine blade.
- the cooling passage at the trailing edge of the wing is divided into a plurality of sections by ribs extending in the direction of the wing.
- the cooling passage at the trailing edge of the wing which is thin and difficult to flow, is relatively widened to facilitate flow, and the tip on the tip side of the rib near the trailing edge is bent toward the corner of the wing.
- the wing trailing edge which usually forms the dead water area, which is the most difficult to flow, intersects with the tip side
- the curved ribs guide the flow to the corners of the wings to guide the flow and allow the cooling steam to sufficiently spread to hard-to-flow areas inside the wings, thereby securing the cooling performance inside the wings and ensuring cooling performance. And a highly reliable turbine blade was obtained.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA002262701A CA2262701C (en) | 1997-06-06 | 1998-06-03 | Gas turbine blade |
US09/230,983 US6257830B1 (en) | 1997-06-06 | 1998-06-03 | Gas turbine blade |
EP98923104A EP0930419A4 (en) | 1997-06-06 | 1998-06-03 | GAS TURBINE DAWN |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP9/149234 | 1997-06-06 | ||
JP14923497A JP3322607B2 (ja) | 1997-06-06 | 1997-06-06 | ガスタービン翼 |
JP27579897A JP3358975B2 (ja) | 1997-10-08 | 1997-10-08 | ガスタービン翼 |
JP9/275798 | 1997-10-08 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1998055735A1 true WO1998055735A1 (fr) | 1998-12-10 |
Family
ID=26479173
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP1998/002454 WO1998055735A1 (fr) | 1997-06-06 | 1998-06-03 | Aube de turbine a gas |
Country Status (4)
Country | Link |
---|---|
US (1) | US6257830B1 (ja) |
EP (1) | EP0930419A4 (ja) |
CA (1) | CA2262701C (ja) |
WO (1) | WO1998055735A1 (ja) |
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JP2000199404A (ja) * | 1998-12-18 | 2000-07-18 | General Electric Co <Ge> | タ―ビン翼形部及び翼形部冷却方法 |
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WO1994012768A2 (en) | 1992-11-24 | 1994-06-09 | United Technologies Corporation | Coolable airfoil structure |
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JPH10280904A (ja) * | 1997-04-01 | 1998-10-20 | Mitsubishi Heavy Ind Ltd | ガスタービン冷却動翼 |
-
1998
- 1998-06-03 CA CA002262701A patent/CA2262701C/en not_active Expired - Fee Related
- 1998-06-03 EP EP98923104A patent/EP0930419A4/en not_active Withdrawn
- 1998-06-03 US US09/230,983 patent/US6257830B1/en not_active Expired - Lifetime
- 1998-06-03 WO PCT/JP1998/002454 patent/WO1998055735A1/ja not_active Application Discontinuation
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JPS55107005A (en) * | 1979-02-13 | 1980-08-16 | United Technologies Corp | Turbine blade |
JPS63120802A (ja) * | 1986-11-07 | 1988-05-25 | Toshiba Corp | ガスタ−ビンの羽根 |
JPH05163959A (ja) * | 1991-12-16 | 1993-06-29 | Tohoku Electric Power Co Inc | タービン静翼 |
JPH08240102A (ja) * | 1995-03-02 | 1996-09-17 | Mitsubishi Heavy Ind Ltd | ガスタービンの蒸気冷却翼 |
JPH08319803A (ja) | 1995-03-31 | 1996-12-03 | General Electric Co <Ge> | 閉回路蒸気冷却動翼 |
JPH08319852A (ja) * | 1995-05-25 | 1996-12-03 | Hitachi Ltd | ガスタービンプラントおよびガスタービンプラントの冷却方法 |
Non-Patent Citations (1)
Title |
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See also references of EP0930419A4 |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2000199404A (ja) * | 1998-12-18 | 2000-07-18 | General Electric Co <Ge> | タ―ビン翼形部及び翼形部冷却方法 |
JP4537518B2 (ja) * | 1998-12-18 | 2010-09-01 | ゼネラル・エレクトリック・カンパニイ | タービン翼形部及び翼形部冷却方法 |
EP1022435A3 (en) * | 1999-01-25 | 2003-12-03 | General Electric Company | Internal cooling circuit for gas turbine bucket |
Also Published As
Publication number | Publication date |
---|---|
CA2262701A1 (en) | 1998-12-10 |
US6257830B1 (en) | 2001-07-10 |
EP0930419A4 (en) | 2001-03-07 |
EP0930419A1 (en) | 1999-07-21 |
CA2262701C (en) | 2003-02-18 |
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