CN111120008B - Novel turbine blade rotational flow cooling structure - Google Patents
Novel turbine blade rotational flow cooling structure Download PDFInfo
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- CN111120008B CN111120008B CN201911259529.4A CN201911259529A CN111120008B CN 111120008 B CN111120008 B CN 111120008B CN 201911259529 A CN201911259529 A CN 201911259529A CN 111120008 B CN111120008 B CN 111120008B
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- jet
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- rotational flow
- cooling cavity
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- 238000001816 cooling Methods 0.000 title claims abstract description 72
- 230000009471 action Effects 0.000 claims abstract description 8
- 230000006866 deterioration Effects 0.000 claims abstract description 7
- 239000012530 fluid Substances 0.000 claims abstract description 6
- 238000000926 separation method Methods 0.000 claims abstract description 4
- 239000007789 gas Substances 0.000 description 9
- 230000000694 effects Effects 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000002776 aggregation Effects 0.000 description 1
- 238000004220 aggregation Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
Classifications
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- 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
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- 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
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- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a novel turbine blade rotational flow cooling structure, which comprises a rotational flow cooling cavity, jet holes and the like; the top of the rotational flow cooling cavity is of a planar structure, and the target surface is of a curved surface structure; the jet holes are arranged on one side of the top surface of the cyclone cooling cavity at equal intervals, the jet grooves are arranged on the other side of the top surface of the cyclone cooling cavity at equal intervals and are opposite to the jet holes, and the jet grooves and the jet holes are arranged in staggered arrangement; the ball socket structures and the air film holes are arranged on the target surface of the cyclone cooling cavity; during operation, the cooling working medium is sprayed from the jet hole to enter the rotational flow cooling cavity, flows along one side of the target surface where the jet hole is located, forms transverse large-scale vortex under the action of the curved target surface, performs strong heat exchange with the target surface, generates flow separation and reattachment when flowing through the ball socket structure, enhances the local heat transfer of the ball socket, obtains higher fluid turbulence energy under the suction action of the air film hole, eliminates the local heat transfer deterioration phenomenon, and discharges the cooling working medium after heat exchange through the outflow groove adjacent to the jet hole.
Description
Technical Field
The invention belongs to the technical field of turbine blade cooling, and particularly relates to a novel turbine blade rotational flow cooling structure.
Background
As one of the core components of the gas turbine, the turbine is closely arranged at the downstream of the combustion chamber, and is continuously flushed by high-temperature and high-pressure gas in the operation process, so that the working environment is extremely bad, and when the turbine is designed, besides taking aerodynamic factors into consideration, the high-efficiency cooling technology is also required to be adopted, so that the temperature of the turbine is reduced to be within the allowable range of materials, and the safe and stable operation of the gas turbine is ensured. The high temperature gas output from the combustion chamber directly impinges on the turbine blade leading edge as it enters the cascade channels, and this region, especially the first stage vane leading edge region, has extremely high thermal loads and is an important concern in blade cooling designs.
In order to improve the cooling performance of the front edge of the turbine blade, an impact cooling mode with the highest enhanced heat transfer effect is often adopted, a plurality of jet holes are formed on the surface of an inner lining plate in the front edge area, cooling air supplied from a blade root is impacted to a front edge bending target surface through the jet holes, strong heat mass exchange is generated in the area near the impact point, and the cooling air absorbs heat from the target surface, so that the temperature of the inner surface and the outer surface of the front edge is effectively reduced.
With the development of gas turbines, the increase in power and efficiency requires the turbine inlet air temperature to be continuously increased according to the inherent laws of the brayton cycle, which presents a great challenge for the cooling design of the turbine components, particularly the cooling design of the leading edge of the turbine first stage guide vanes. Because the traditional impingement cooling can not cope with the rapid rise of the thermal load of the front edge of the blade in many cases, related experts and designers propose a rotational flow cooling structure, namely jet holes are arranged in the area of one side of the top surface, and cooling working media enter the channel and then form a transverse large-scale vortex system along the arc target surface, so that the turbulent kinetic energy of fluid is enhanced, and the cooling performance obviously superior to that of the traditional impingement structure is obtained.
However, the adoption of the cyclone cooling structure can generate local heat transfer deterioration among jet holes, so that the non-uniformity of the temperature distribution of the front edge of the blade is aggravated, and meanwhile, the cross flow formed by the aggregation of upstream cyclone working media can obviously weaken the intensified heat transfer function of downstream jet flow, so that the potential cooling performance of the cyclone structure can not be fully exerted. Therefore, there is a strong need for a new turbine blade swirling cooling structure that achieves improved swirling cooling performance by overcoming the above-mentioned problems, thereby achieving efficient thermal protection of the turbine blade leading edge.
Disclosure of Invention
In order to solve the problems, the invention provides a novel turbine blade cyclone cooling structure, which eliminates the influence of cross flow through a distributed outflow groove, avoids the rapid attenuation of the cyclone heat transfer performance in the flow direction, improves the overall heat transfer level, and reduces the pressure loss; the ball socket and air film hole combined structure of the target surface enhances local heat transfer, obviously reduces the heat transfer deterioration area of the traditional rotational flow target surface, improves the heat transfer performance and reduces the temperature difference of the target surface at the same time, thereby improving the overall cooling performance.
The invention is realized by adopting the following technical scheme:
A novel turbine blade rotational flow cooling structure comprises a rotational flow cooling cavity, jet holes, a flow outlet groove, a ball socket structure and a gas film hole; the top of the rotational flow cooling cavity is of a planar structure, and the target surface is of a curved surface structure; the jet holes are arranged on one side of the top surface of the cyclone cooling cavity at equal intervals, the jet grooves are arranged on the other side of the top surface of the cyclone cooling cavity at equal intervals and are opposite to the jet holes, and the jet grooves and the jet holes are arranged in staggered arrangement; the ball socket structures and the air film holes are arranged on the target surface of the cyclone cooling cavity;
During operation, the cooling working medium is sprayed from the jet hole to enter the rotational flow cooling cavity, flows along one side of the target surface where the jet hole is located, forms transverse large-scale vortex under the action of the curved target surface, performs strong heat exchange with the target surface, generates flow separation and reattachment when flowing through the ball socket structure, enhances the local heat transfer of the ball socket, obtains higher fluid turbulence energy under the suction action of the air film hole, eliminates the local heat transfer deterioration phenomenon, and discharges the cooling working medium after heat exchange through the outflow groove adjacent to the jet hole.
The invention is further improved in that the target surface shape of the cyclone cooling cavity adopts an arc, an elliptic arc, a parabola or a hyperbola.
The invention is further improved in that the jet holes are rectangular, straight slot-shaped, round and oval, the ratio S/w of the arrangement space of the jet holes to the width of the jet holes is in the range of 2-5, and the ratio w/t of the width of the jet holes to the thickness of the jet holes is in the range of 1-6.
The invention is further improved in that the outflow slot is arranged on the other side of the area between adjacent jet holes, and the outflow slot is rectangular, straight slot-shaped, round and oval, and has the same structural size and arrangement mode as the jet holes.
The invention is further improved in that the ball-and-socket structure is arranged in the target surface area between the adjacent jet holes, the depth-to-diameter ratio e/D d of the ball-and-socket structure (4) is in the range of 0.1-0.3, the ball-and-socket structure is uniformly arranged in the circumferential direction of the target surface, and the circumferential arrangement quantity is 1-6.
The invention is further improved in that the air film holes are arranged in the target surface area between the adjacent jet holes, the cross section of the air film holes is circular or elliptical, the arrangement angle alpha of the air film holes is changed within the range of 0-180 degrees, and the circumferential arrangement number of the air film holes is 1-4.
A further development of the invention is that the gas film holes are arranged on the surface of the ball socket structure or in the target area in the vicinity of the ball socket structure.
The invention has at least the following beneficial technical effects:
The turbine blade cyclone cooling structure provided by the invention is introduced with a plurality of distributed outflow grooves, and cooling working media injected into the channels by the jet holes can be discharged through the outflow grooves after heat exchange is finished, so that cross flow commonly existing in the traditional cyclone channels is not formed, the weakening effect of the cross flow on downstream heat transfer can be eliminated, the impact cyclone can keep a better enhanced heat transfer effect in the radial direction, and the overall heat transfer performance of the target surface is obviously improved.
Furthermore, the flexible and variable target surface shape can adapt to different blade front edge molded lines, so that the height adaptation with the turbine blade front edge structure is realized, and the shape and the structural size of the jet hole and the jet slot can be selected according to the heated load of the front edge when the turbine runs, so that the adaptability and the cooling performance of the novel rotational flow structure are improved to the greatest extent;
Furthermore, the ball socket structure has the advantages of high heat transfer and low flow resistance, only small resistance loss is generated while the heat transfer is enhanced, meanwhile, the heat transfer area can be increased, and the ball socket structure is arranged on the target surface of the cyclone cooling cavity to realize the control of local flow heat transfer, so that the heat transfer deterioration area is eliminated, and the heat transfer level is improved and the more uniform temperature distribution is realized;
Furthermore, the suction effect of the air film holes can enhance the turbulence energy of fluid in the nearby area, destroy the flowing boundary layer, promote the heat exchange near the wall surface, and in addition, the air film holes can also form a protective air film on the outer surface of the blade, weaken the heat exchange between high-temperature fuel gas and the blade, and realize efficient internal and external coupling cooling.
From the above, the invention establishes a novel turbine blade rotational flow cooling structure, eliminates the negative influence of cross flow in the traditional rotational flow channel on heat transfer through the distributed outflow grooves, so that high heat transfer level is maintained in the whole channel, and meanwhile, the arrangement of the ball socket structure and the air film holes realizes local flow control, so that the heat transfer performance is improved, and meanwhile, more uniform temperature distribution can be obtained, thereby realizing better comprehensive cooling performance.
Drawings
FIG. 1 is a three-dimensional view of a turbine blade rotational flow cooling structure;
FIG. 2 is a schematic illustration of the arrangement of jet holes and outflow slots on the top surface of a channel;
FIG. 3 is a schematic view of an orifice and an outflow slot, wherein FIG. 3 (a) is a rectangular orifice/outflow slot, FIG. 3 (b) is a straight slot shaped orifice/outflow slot, FIG. 3 (c) is a circular orifice/outflow slot, and FIG. 3 (d) is an elliptical orifice/outflow slot;
FIG. 4 is a schematic view of a ball and socket structure and air film hole arrangement in a localized area of the target surface;
FIG. 5 is a schematic cross-sectional view of a ball and socket arrangement;
FIG. 6 is a schematic cross-sectional view of a gas film hole structure and arrangement.
Reference numerals illustrate:
1 is a rotational flow cooling cavity, 2 is a jet hole, 3 is a jet slot, 4 is a ball-and-socket structure, 5 is a gas film hole, 231 is a rectangular jet hole/jet slot, 232 is a straight slot-shaped jet hole/jet slot, 233 is a circular jet hole/jet slot, and 234 is an elliptical jet hole/jet slot.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings.
Referring to fig. 1 and 2, the novel turbine blade rotational flow cooling structure provided by the invention comprises a rotational flow cooling cavity 1, a plurality of jet holes 2, a plurality of outflow grooves 3, a plurality of ball socket structures 4 and a plurality of air film holes 5. The top of the cyclone cooling cavity 1 is of a planar structure, and the target surface is of a curved surface structure; the jet holes 2 are arranged on one side of the top surface of the cyclone cooling cavity 1 at equal intervals, the outflow grooves 3 are arranged on the other side of the top surface of the cyclone cooling cavity 1 opposite to the jet holes 2 at equal intervals, and the outflow grooves 3 and the jet holes 2 are arranged in staggered mode; and a plurality of ball socket structures 4 and air film holes 5 are arranged on the target surface of the cyclone cooling cavity 1. The whole flow heat transfer process is as follows: the cooling working medium is sprayed from the jet hole 2 into the rotational flow cooling cavity 1, flows along one side of the target surface where the jet hole 2 is positioned, forms transverse large-scale vortex under the action of the curved target surface, performs strong heat exchange with the target surface, generates flow separation and reattachment when flowing through the ball socket structure 4, enhances the local heat transfer of the ball socket, obtains higher fluid turbulence energy under the suction action of the air film hole 5, eliminates the local heat transfer deterioration phenomenon, and discharges the cooling working medium after heat exchange through the outflow groove 3 adjacent to the jet hole 2.
The target surface shape can be in the form of circular arc, elliptic arc, parabola, hyperbola or other curve similar to the front edge structure of the turbine blade.
Referring to fig. 2 and 3, the shape of the jet holes 2 may be rectangular, straight slot, circular, oval, etc., and the ratio S/w of the arrangement pitch of the jet holes 2 to the width of the jet holes 2 is preferably in the range of 2 to 5, and the ratio w/t of the width of the jet holes 2 to the thickness is preferably in the range of 1 to 6. The outflow slot 3 is arranged at the other side of the area between the adjacent jet holes 2, and the shape of the outflow slot can be rectangular, straight slot-shaped, round, elliptic and the like, and the structural size and the arrangement mode are the same as those of the jet holes 2. Accordingly, the present invention has a rectangular jet hole/outflow slot 231, a straight slot-shaped jet hole/outflow slot 232, a circular jet hole/outflow slot 233, and an elliptical jet hole/outflow slot 234.
Referring to fig. 1, 4, 5 and 6, the ball and socket structure 4 is disposed in a target surface region between adjacent jet holes 2, the depth-to-diameter ratio e/D d of the ball and socket structure 4 is preferably in the range of 0.1 to 0.3, it is uniformly disposed in the circumferential direction of the target surface, and the number of circumferential dispositions is preferably 1 to 6. The air film holes 5 are arranged in the target surface area between the adjacent jet holes 2, the cross section shape of the air film holes can be circular, elliptic and the like, the arrangement angle alpha of the air film holes 5 can be changed within the range of 0-180 degrees, and the circumferential arrangement quantity of the air film holes 5 is preferably 1-4. The air film holes 5 can be arranged on the surface of the ball socket structure 4, and can also be arranged in the target surface area near the ball socket.
Claims (4)
1. The novel turbine blade rotational flow cooling structure is characterized by comprising a rotational flow cooling cavity (1), jet holes (2), outflow grooves (3), ball socket structures (4) and air film holes (5); wherein,
The top of the rotational flow cooling cavity (1) is of a plane structure, and the target surface is of a curved surface structure; the jet holes (2) are arranged on one side of the top surface of the cyclone cooling cavity (1) at equal intervals, the outflow grooves (3) are arranged on the other side of the top surface of the cyclone cooling cavity (1) opposite to the jet holes (2) at equal intervals, and the outflow grooves (3) and the jet holes (2) are arranged in staggered mode; the ball socket structures (4) and the air film holes (5) are arranged on the target surface of the cyclone cooling cavity (1);
During operation, a cooling working medium is sprayed into the rotational flow cooling cavity (1) from the jet hole (2), flows along one side of the target surface where the jet hole (2) is positioned, forms transverse large-scale vortex under the action of the curved target surface, performs strong heat exchange with the target surface, generates flow separation and reattachment when flowing through the ball socket structure (4), enhances the local heat transfer of the ball socket, obtains higher fluid turbulence energy under the suction action of the air film hole (5), eliminates the local heat transfer deterioration phenomenon, and the cooling working medium after completing heat exchange is discharged through the outflow groove (3) adjacent to the jet hole (2);
the outflow slot (3) is arranged at the other side of the area between the adjacent jet holes (2), the shape of the outflow slot is rectangular, straight slot-shaped, round and oval, and the structural size and the arrangement mode are the same as those of the jet holes (2);
the air film holes (5) are arranged in a target surface area between adjacent jet holes (2), the cross section of the air film holes is circular or elliptical, the arrangement angle alpha of the air film holes (5) is changed within the range of 0-180 degrees, and the circumferential arrangement number of the air film holes (5) is 1-4;
the air film hole (5) is arranged on the surface of the ball socket structure (4) or is arranged in a target surface area near the ball socket structure (4).
2. The novel turbine blade rotational flow cooling structure according to claim 1, wherein the target surface shape of the rotational flow cooling cavity (1) adopts an arc, an elliptical arc, a parabola or a hyperbola.
3. The novel turbine blade rotational flow cooling structure according to claim 1, wherein the jet holes (2) are rectangular, straight slot-shaped, circular and oval in shape, the ratio S/w of the arrangement interval of the jet holes (2) to the jet hole width is in the range of 2-5, and the ratio w/t of the jet hole width to the thickness is in the range of 1-6.
4. The novel turbine blade rotational flow cooling structure according to claim 1, wherein ball and socket structures (4) are arranged in target surface areas between adjacent jet holes (2), the depth-to-diameter ratio e/D d of the ball and socket structures (4) is in the range of 0.1-0.3, the ball and socket structures are uniformly arranged in the circumferential direction of the target surface, and the number of the circumferential arrangements is 1-6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911259529.4A CN111120008B (en) | 2019-12-10 | 2019-12-10 | Novel turbine blade rotational flow cooling structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911259529.4A CN111120008B (en) | 2019-12-10 | 2019-12-10 | Novel turbine blade rotational flow cooling structure |
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| Publication Number | Publication Date |
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| CN111120008A CN111120008A (en) | 2020-05-08 |
| CN111120008B true CN111120008B (en) | 2024-10-25 |
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| CN201911259529.4A Active CN111120008B (en) | 2019-12-10 | 2019-12-10 | Novel turbine blade rotational flow cooling structure |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112302727A (en) * | 2020-11-23 | 2021-02-02 | 华能国际电力股份有限公司 | Turbine blade leading edge cooling structure |
| CN113266427B (en) * | 2021-04-28 | 2022-07-12 | 西安交通大学 | Inside compound cooling structure of turbine movable vane |
| CN113404546A (en) * | 2021-07-09 | 2021-09-17 | 中国联合重型燃气轮机技术有限公司 | Blade, turbine and gas turbine |
| CN113404545A (en) * | 2021-07-09 | 2021-09-17 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and turbine blade thereof |
| CN114109518A (en) * | 2021-11-29 | 2022-03-01 | 西安交通大学 | Turbine blade leading edge ribbed rotational flow-air film composite cooling structure |
| CN114215607A (en) * | 2021-11-29 | 2022-03-22 | 西安交通大学 | Turbine blade leading edge rotational flow cooling structure |
| CN115045721B (en) * | 2022-08-17 | 2022-12-06 | 中国航发四川燃气涡轮研究院 | Series-type rotational flow impact turbine blade cooling unit and turbine blade |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN211008774U (en) * | 2019-12-10 | 2020-07-14 | 西安交通大学 | Novel turbine blade rotational flow cooling structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US7008179B2 (en) * | 2003-12-16 | 2006-03-07 | General Electric Co. | Turbine blade frequency tuned pin bank |
| US8794906B1 (en) * | 2010-06-22 | 2014-08-05 | Florida Turbine Technologies, Inc. | Turbine stator vane with endwall cooling |
| US8858176B1 (en) * | 2011-12-13 | 2014-10-14 | Florida Turbine Technologies, Inc. | Turbine airfoil with leading edge cooling |
| EP2682565B8 (en) * | 2012-07-02 | 2016-09-21 | General Electric Technology GmbH | Cooled blade for a gas turbine |
| CN103452595A (en) * | 2013-09-25 | 2013-12-18 | 青岛科技大学 | Novel air film hole with improved cooling efficiency |
| CN106168143B (en) * | 2016-07-12 | 2017-12-15 | 西安交通大学 | A kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket |
| CN108150224A (en) * | 2017-12-21 | 2018-06-12 | 西安交通大学 | A kind of eddy flow is the same as impacting cooling structure inside the turbine blade being combined |
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| CN211008774U (en) * | 2019-12-10 | 2020-07-14 | 西安交通大学 | Novel turbine blade rotational flow cooling structure |
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