CN109763864A - A kind of turbine stator vane, turbine stator vane cooling structure and cooling means - Google Patents
A kind of turbine stator vane, turbine stator vane cooling structure and cooling means Download PDFInfo
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- CN109763864A CN109763864A CN201811598080.XA CN201811598080A CN109763864A CN 109763864 A CN109763864 A CN 109763864A CN 201811598080 A CN201811598080 A CN 201811598080A CN 109763864 A CN109763864 A CN 109763864A
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Abstract
This application discloses a kind of turbine stator vane, turbine stator vane cooling structure and cooling means, wherein it is cooling radially to carry out subregion by cooling medium to the inside of turbine stator vane along turbine for cooling means, each subregion uses different cooling mediums, and radially direction from inside to outside, the evaporating temperature of cooling medium are gradually increased.Due to radial from inside to outside along turbine, the temperature of turbine stator vane is from low to high, this method is according to the radial different cooling requirement in each position of turbine stator vane, realize that subregion is cooling by the cooling medium that evaporating temperature is gradually increased in each subregion, improve cooling efficiency, and energy matching degree is maximumlly improved, avoid energy waste.
Description
Technical field
The present invention relates to aero-turbine blade cooling technologies field, in particular to a kind of turbine stator vane is cold
But method.The invention further relates to a kind of turbine stator vane cooling structures based on turbine stator vane cooling means.The present invention
Further relate to a kind of turbine stator vane comprising the turbine stator vane cooling structure.
Background technique
Aero-engine gas-turbine blade subjects the effect of the high temperature and high pressure gas from combustion chamber, so that common
Blade material heatproof degree nearly reaches the limit, using efficient technique for cooling blades be improve turbo blade service life and
Improve the important means of turbine inlet temperature.
Currently, with the development of technique for cooling blades, cooling is carried out to turbine stator vane based on hot tube high-efficiency heat exchange
Mode is come into being.However, being exchanged heat at present using hot tube high-efficiency, there is also following deficiencies for cooling turbine stator vane: due to heat
The shape of pipe is more limited to, it is difficult to accomplish the uniform cooling to blade, thermal stress distribution is uneven；At the different location of blade
Temperature difference is larger, using single liquid heat transfer medium and liquid-sucking core, is easy to cause heat exchange when using in wide temperature range
Inefficiency, and the problems such as heat transferring medium and vulnerable liquid-sucking core.
Summary of the invention
In view of this, the purpose of the present invention is to provide a kind of turbine stator vane cooling means, to improve stators
The cooling efficiency of blade.
It is another object of the present invention to provide a kind of stators leaves based on the turbine stator vane cooling means
Piece cooling structure, to improve the cooling efficiency of turbine stator vane.
Third object of the present invention is to provide a kind of stators leaf comprising the turbine stator vane cooling structure
Piece, to improve the cooling efficiency of turbine stator vane.
In order to achieve the above objectives, the present invention the following technical schemes are provided:
A kind of turbine stator vane cooling means, by cooling medium to the inside of turbine stator vane along turbine radial direction
It is cooling to carry out subregion, each subregion uses different cooling mediums, and radially direction from inside to outside, the cooling medium
Evaporating temperature is gradually increased.
The present invention also provides a kind of turbine stator vane cooling structures, the blade including being set to turbine stator vane
It is internal and include being located at radially inner side along multiple cooling cavities that turbine is radially successively arranged, each cooling cavities
Condensation segment and evaporator section positioned at radial outside, be filled with cooling medium in each cooling cavities, it is described cooling to be situated between
Matter is condensed into liquid in the condensation segment, is evaporated to gas in the evaporator section；Along the radial direction from inside to outside of turbine, respectively
The evaporating temperature of the intracorporal cooling medium of cooling chamber is gradually increased.
Preferably, it in above-mentioned turbine stator vane cooling structure, is provided with and is used in each cooling cavities
Cooling medium attraction in the condensation segment is transferred to the wicking structure being evaporated in the evaporator section.
Preferably, in above-mentioned turbine stator vane cooling structure, along the radial direction from inside to outside of turbine, each institute
The imbibition ability for stating the intracorporal wicking structure of cooling chamber gradually increases.
Preferably, in above-mentioned turbine stator vane cooling structure, the wicking structure is to be set to the cooling chamber
Mesh members on the inner wall of body；Or the wicking structure is the groove structure being set on the inner wall of the cooling cavities；
Or the wicking structure is the mesh members being set on the inner wall of the cooling cavities and the composite construction of groove structure.
Preferably, in above-mentioned turbine stator vane cooling structure, the cooling medium is alcohols, water, benzene class, water
Silver, alkali metal or silver.
Preferably, radial from inside to outside along turbine in above-mentioned turbine stator vane cooling structure, each cooling
The radial height of cavity is gradually increased.
Preferably, radial from inside to outside along turbine in above-mentioned turbine stator vane cooling structure, each cooling
The thickness of the radially inner side cavity wall of cavity is gradually reduced.
Preferably, in above-mentioned turbine stator vane cooling structure, the shape of the cooling cavities and the blade
Shape matches.
The present invention also provides a kind of turbine stator vanes, the platform including blade and positioned at the root of the blade, institute
It states blade and is provided with cooling structure, which is characterized in that the cooling structure is the turbine stator vane as described in any of the above item
Cooling structure.
Preferably, in above-mentioned turbine stator vane, the condensation segment close to the cooling cavities of the platform is located at
In the platform.
Preferably, in above-mentioned turbine stator vane, vent rib is additionally provided on the outer wall of the blade.
Compared with prior art, the beneficial effects of the present invention are:
Turbine stator vane cooling means provided by the invention are as follows: by cooling medium to the inside of turbine stator vane
It is cooling that subregion is radially carried out along turbine, each subregion uses different cooling mediums, and radially direction from inside to outside, cooling
The evaporating temperature of medium is gradually increased.Due to radial from inside to outside along turbine, the temperature of turbine stator vane from low to high, should
Method according to the radial different cooling requirement in each position of turbine stator vane, by each subregion evaporating temperature be gradually increased
Cooling medium realize that subregion is cooling, improve cooling efficiency, and maximumlly improve energy matching degree, avoid energy waste.
In turbine stator vane cooling structure provided by the invention, inside blade along turbine radially successively arrange it is multiple cold
But cavity includes the evaporator section positioned at the condensation segment of radially inner side and positioned at radial outside, Mei Geleng in each cooling cavities
But cooling medium is filled in cavity, cooling medium is condensed into liquid in condensation segment, is evaporated to gas in evaporator section；Along whirlpool
The evaporating temperature in the direction of wheel radial from inside to outside, each intracorporal cooling medium of cooling chamber is gradually increased.The turbine stator vane
Cooling structure passes through the evaporating temperature in each cooling cavities according to the radial different cooling requirement in each position of turbine stator vane
The cooling medium being gradually increased realizes that subregion is cooling, improves cooling efficiency, and maximumlly improves energy matching degree, avoids
Energy waste.
Turbine stator vane provided by the invention uses the turbine stator vane cooling structure in the application, therefore, root
According to turbine stator vane, radially the different cooling requirement in each position carries out subregion cooling, improves cooling efficiency.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will to embodiment or
Attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
The embodiment of the present invention for those of ordinary skill in the art without creative efforts, can be with
Other attached drawings are obtained according to the attached drawing of offer.
Fig. 1 is a kind of internal cross section schematic diagram of turbine stator vane provided in an embodiment of the present invention；
Fig. 2 is the internal cross section schematic diagram of another turbine stator vane provided in an embodiment of the present invention.
Wherein, 1 it is turbine stator vane, 2 be blade, 3 be platform, 4 be the first cavity, 5 be the second cavity, 6 is third
Cavity, 7 be the 4th cavity, 8 be the 5th cavity.
Specific embodiment
Core of the invention improves the cold of turbine stator vane there is provided a kind of turbine stator vane cooling means
But efficiency.
The present invention also provides a kind of turbine stator vane cooling structure based on the turbine stator vane cooling means,
Improve the cooling efficiency of turbine stator vane.
The present invention also provides a kind of turbine stator vanes comprising the turbine stator vane cooling structure, improve turbine
The cooling efficiency of stator blade.
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts it is all its
His embodiment, shall fall within the protection scope of the present invention.
Fig. 1 and Fig. 2 are please referred to, the embodiment of the invention provides a kind of turbine stator vane cooling means, are situated between by cooling
The inside of confrontation turbine stator vane 1 radially carries out subregion cooling along turbine, and each subregion uses different cooling mediums, and
The evaporating temperature in radially direction from inside to outside, cooling medium is gradually increased.
Due to radial from inside to outside along turbine, from low to high, this method is quiet according to turbine for the temperature of turbine stator vane 1
The different cooling requirement in the radial each position of blades 1, is realized by the cooling medium that evaporating temperature is gradually increased in each subregion
Subregion is cooling, improves cooling efficiency, and maximumlly improves energy matching degree, avoids energy waste.
Based on above-mentioned turbine stator vane cooling means, the embodiment of the invention also provides a kind of turbine stator vane is cold
But structure blade 2 inside and multiple cooling cavities for radially successively arranging along turbine including be set to turbine stator vane 1,
Each cooling cavities is isolated from each other, the quantity of cooling cavities can for three, four, five, six etc. more, turbine is radial
The as root of blade 2 to the direction of blade tip is inside close to the root of blade 2, and the blade tip close to blade 2 is outside, each
It include the condensation segment positioned at radially inner side and evaporator section positioned at radial outside in cooling cavities, in each cooling cavities
Filled with cooling medium, cooling medium is condensed into liquid in condensation segment, is evaporated to gas in evaporator section；It is radial by interior along turbine
The evaporating temperature of outwardly direction, each intracorporal cooling medium of cooling chamber is gradually increased, i.e., cold along the root of blade 2 to blade tip
But the evaporating temperature of the intracorporal cooling medium of chamber itself is gradually increased.
The working principle of the turbine stator vane cooling structure is: the cooling medium in each cooling cavities is in condensation segment
It is condensed into liquid to the cold, is evaporated to gas in evaporator section heat, so recycles, realizes the respective cooling of each cooling cavities
Circulation.Since the root temperature of blade 2 is lower than the temperature of blade tip, and the temperature difference difference it is larger, therefore, blade 2 radially inside
Multiple cooling cavities are separated out, the evaporation temperature of the cooling medium itself in the direction that temperature gradient increases, these cooling cavities
Degree, i.e. boiling point, are gradually increased, to match the cooling requirement of each temperature section.It is changed compared to only with a kind of liquid
Heat, it is cooling using subregion, cooling efficiency is improved, cooling effect is improved, and maximumlly improves energy matching degree, is avoided
Energy waste.It, can be after there are also the cooling medium in other cooling cavities when the cooling medium failure in some cooling cavities
Continuous work, reduces the cooling adverse effect to blade.
Further, in the present embodiment, it is provided in each cooling cavities for by the cooling medium in condensation segment
Attraction is transferred to the wicking structure being evaporated in evaporator section.Cooling medium can be more advantageous to by wicking structure condensing
The conversion of transfer and state between section and evaporator section, heat exchange efficiency are higher.It is of course also possible to it is not provided with wicking structure, but
Transfer is realized by cooling medium natural evaporation and condensation, but cooling efficiency is not so good as the height provided with wicking structure.
When being provided with wicking structure in each cooling cavities, if the wicking structure in some cooling cavities fails,
It can individually be replaced, reduce maintenance cost, and will not have an impact to the cooling of other cooling cavities.
Further, in the present embodiment, inwardly there are outside direction, each intracorporal imbibition of cooling chamber along turbine diameter
The imbibition ability of structure gradually increases.According to blade 2 by the constantly raised temperature in root to blade tip, in different cooling cavities
The different wicking structure of interior setting, close to the lower position of 2 root temperature of blade, setting cost is lower, imbibition effect is weaker
Wicking structure, close to blade tip extreme temperatures position, select the stronger wicking structure of imbibition effect, can preferably mention
The cooling effect of high blade.
In the present embodiment, wicking structure is the mesh members being set on the inner wall of cooling cavities, specially stainless steel
Mesh members, mesh members have many advantages, such as that structure is simple, easily manufactured, low in cost；Wicking structure is cold to be set to
But the groove structure on the inner wall of cavity, its main feature is that thermal resistance is small, suitability for secondary processing is good；Or wicking structure is to be set to
The composite construction of mesh members and groove structure on the inner wall of cooling cavities, the structure reach the performance of wicking structure
It is optimal, it can guarantee that the permeability of wicking structure and capillary pressure all reach ideal value under hot conditions.The imbibition of mesh members
Ability is weaker than the imbibition ability of groove structure, and the imbibition ability of groove structure is weaker than the compound of mesh members and groove structure
The imbibition ability of structure.By mesh members, the permeability of groove structure and capillarity realize cooling medium from condensation segment to
The transfer of evaporator section, the gas of evaporation complete circulation by returning to condensation segment in the middle part of cooling cavities.
In the present embodiment, cooling medium is alcohols, water, sulphur, Dowtherm, benzene class, mercury, alkali metal or silver.Specifically
Ground, alcohols can be methanol, ethyl alcohol；Benzene class can be toluene, and alkali metal can be lithium metal, metallic sodium, metal caesium.According to
The cooling medium of the temperature selection appropriate evaporation temperature of different cooling cavities.
In the present embodiment, radial from inside to outside along turbine, the radial height of each cooling cavities is gradually increased.Due to leaning on
Nearly radially inner side cooling requirement is small, and the cross-sectional area of blade 2 is big, so desirable smaller of the radial height of cooling cavities,
Bigger close to radial outside cooling requirement, and the cross-sectional area of blade 2 is small, so desirable larger of the height of cooling cavities,
To improve cooling effect.
Similarly, in the present embodiment, radial from inside to outside along turbine, the thickness of the radially inner side cavity wall of each cooling cavities
Degree is gradually reduced, to improve cooling effect.
Further, in the present embodiment, the shape of cooling cavities and the shape of blade 2 match.So set, can
So that the uniform wall thickness of cooling cavities keeps thermal stress distribution more equal to realize the uniform cooling at each position of cooling cavities
It is even.
Below in case where when cooling cavities is three and five, it is illustrated:
As shown in Figure 1, that is, radial along turbine is successively the first chamber from inside to outside when the quantity of cooling cavities is three
Body 4, the second cavity 5 and third cavity 6；Cooling medium in the first cavity 4 is ethyl alcohol, water or toluene, and operating temperature is low
In 400 DEG C, wicking structure is mesh members；Cooling medium in the second cavity 5 is sulphur or Dowtherm, operating temperature
At 400~100 DEG C, wicking structure is groove structure；Cooling medium in third cavity 6 be lithium metal, metallic sodium or
Silver, operating temperature are higher than 1000 DEG C, and wicking structure is the composite construction of mesh members and groove structure.
The radial height for taking the first cavity 4 is H01, the radial height of the second cavity 5 is H02, the radial height of third cavity 6
Degree is H03, the height of blade 2 is H, to realize maximum heat exchange amount and heat exchange efficiency, it is desirable that 0 < H01<H02<H03<H。
Take the radially inner side cavity wall of the first cavity 4 with a thickness of L01, i.e., radial direction between 3 bottom surface of platform and the first cavity 4
Distance is L01；The thickness L of the radially inner side cavity wall of second cavity 512, i.e. between the first cavity 4 and the second cavity 5 it is radial away from
From for L12；The radially inner side cavity wall of third cavity 6 with a thickness of L23, i.e., between the second cavity 5 and third cavity 6 it is radial away from
From for L23；The radial outside cavity wall of third cavity 6 with a thickness of L30, i.e., between 2 tip of third cavity 6 and blade it is radial away from
From for L30, then L01>L12>L23>L30。
As shown in Fig. 2, that is, radial along turbine is successively the first chamber from inside to outside when the quantity of cooling cavities is five
Body 4, the second cavity 5, third cavity 6, the 4th cavity 7 and the 5th cavity 8；Cooling medium in the first cavity 4 is methanol
Or ethyl alcohol, operating temperature are lower than 200 DEG C, wicking structure is mesh members；Cooling medium in the second cavity 5 be water or
Person's mercury, operating temperature are 200~400 DEG C, and wicking structure is mesh members；Cooling medium in third cavity 6 is gold
Belong to caesium or metallic potassium, operating temperature is 400~1000 DEG C, and wicking structure is groove structure；Cooling in the 4th cavity 7
Medium is lithium metal, and operating temperature is 1000~1800 DEG C, and wicking structure is the composite construction of mesh members and groove structure；
Cooling medium in the 5th cavity 8 is metallic silver, and operating temperature is 1800 DEG C or more, wicking structure be mesh members and
The composite construction of groove structure.
The radial height for taking the first cavity 4 is H01, the radial height of the second cavity 5 is H02, the radial height of third cavity 6
Degree is H03, the radial height of the 4th cavity 7 is H04, the height of the 5th cavity 8 is H05, the height of blade 2 is H, to realize most
Big heat exchange amount and heat exchange efficiency, it is desirable that 0 < H01<H02<H03<H04< H05<H。
Take the radially inner side cavity wall of the first cavity 4 with a thickness of L01, i.e., radial direction between 3 bottom surface of platform and the first cavity 4
Distance is L01；The thickness L of the radially inner side cavity wall of second cavity 512, i.e. between the first cavity 4 and the second cavity 5 it is radial away from
From for L12；The radially inner side cavity wall of third cavity 6 with a thickness of L23, i.e., between the second cavity 5 and third cavity 6 it is radial away from
From for L23；The radially inner side cavity wall of 4th cavity 6 with a thickness of L34, i.e., between third cavity 6 and the 4th cavity 7 it is radial away from
From for L34；The radially inner side cavity wall of 5th cavity 8 with a thickness of L45, i.e., between the 4th cavity 7 and the 5th cavity 8 it is radial away from
From for L45；The radial outside cavity wall of 5th cavity 8 with a thickness of L50, i.e. the radial distance of the 5th cavity 8 and blade tip is L50, then
L01> L12>L23>L34>L45>L50。
In fig. 1 and 2, the section of blade 2 is trapezoidal, and therefore, the cross sectional shape of cooling cavities is similarly trapezoidal, cold
But the shape of cavity and the shape of blade 2 match.
As depicted in figs. 1 and 2, based on a kind of turbine stator vane 1 described in any of the above embodiment, including blade 2
With the platform 3 for the root for being located at blade 2, blade 2 is provided with cooling structure, then cooling structure is as any of the above embodiment is retouched
The turbine stator vane cooling structure stated.
Since turbine stator vane 1 uses the turbine stator vane cooling structure in the application, according to turbine
The different cooling requirement in the radial each position of stator blade 1 carries out subregion cooling, improves cooling efficiency.
Further, in the present embodiment, it is located in platform 3 close to the condensation segment of the cooling cavities of platform 3, to subtract
Radial distance between the bottom surface of chain-wales 3 and the cooling cavities improves the cooling effect at the position.And the cooling cavities
Rest part shape and the shape of blade 2 match.
Further, in the present embodiment, the outer wall of cooling cavities can be equipped with multiple vent ribs, with enhanced heat exchange.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with its
The difference of his embodiment, the same or similar parts in each embodiment may refer to each other.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, defined herein
General Principle can realize in other embodiments without departing from the spirit or scope of the present invention.Therefore, originally
Invention is not intended to be limited to the embodiments shown herein, and is to fit to special with principles disclosed herein and novelty
The consistent widest scope of point.
Claims (10)
1. a kind of turbine stator vane cooling means, which is characterized in that by cooling medium to the inside edge of turbine stator vane
Turbine radially carries out subregion cooling, and each subregion uses different cooling mediums, and radially direction from inside to outside, the cooling
The evaporating temperature of medium is gradually increased.
2. a kind of turbine stator vane cooling structure, which is characterized in that including being set to inside the blade of turbine stator vane and
It include the condensation segment positioned at radially inner side along the radial multiple cooling cavities successively arranged of turbine, in each cooling cavities
With the evaporator section for being located at radial outside, cooling medium is filled in each cooling cavities, the cooling medium is described
Condensation segment is condensed into liquid, is evaporated to gas in the evaporator section；Along the radial direction from inside to outside of turbine, each cooling chamber
The evaporating temperature of intracorporal cooling medium is gradually increased.
3. turbine stator vane cooling structure according to claim 2, which is characterized in that in each cooling cavities
It is provided with for the cooling medium attraction in the condensation segment to be transferred to the wicking structure being evaporated in the evaporator section, edge
The radial direction from inside to outside of turbine, the imbibition ability of each intracorporal wicking structure of cooling chamber gradually increase.
4. turbine stator vane cooling structure according to claim 3, which is characterized in that the wicking structure is to be set to
Mesh members on the inner wall of the cooling cavities；Or the wicking structure is to be set on the inner wall of the cooling cavities
Groove structure；Or the wicking structure is answering for the mesh members being set on the inner wall of the cooling cavities and groove structure
Close structure.
5. according to the described in any item turbine stator vane cooling structures of claim 2-4, which is characterized in that the cooling medium
For alcohols, water, benzene class, mercury, alkali metal or silver.
6. according to the described in any item turbine stator vane cooling structures of claim 2-4, which is characterized in that along turbine it is radial by
From inside to outside, the radial height of each cooling cavities is gradually increased.
7. according to the described in any item turbine stator vane cooling structures of claim 2-4, which is characterized in that along turbine it is radial by
From inside to outside, the thickness of the radially inner side cavity wall of each cooling cavities is gradually reduced.
8. according to the described in any item turbine stator vane cooling structures of claim 2-4, which is characterized in that the cooling cavities
Shape and the shape of the blade match.
9. a kind of turbine stator vane, the platform including blade and positioned at the root of the blade, the blade are provided with cooling
Structure, which is characterized in that the cooling structure is such as the described in any item turbine stator vane cooling structures of claim 1-8.
10. turbine stator vane according to claim 9, which is characterized in that close to the cooling cavities of the platform
Condensation segment be located in the platform, be provided with vent rib on the outer wall of the blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811598080.XA CN109763864A (en) | 2018-12-26 | 2018-12-26 | A kind of turbine stator vane, turbine stator vane cooling structure and cooling means |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201811598080.XA CN109763864A (en) | 2018-12-26 | 2018-12-26 | A kind of turbine stator vane, turbine stator vane cooling structure and cooling means |
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| CN109763864A true CN109763864A (en) | 2019-05-17 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2098556U (en) * | 1991-06-01 | 1992-03-11 | 西安交通大学 | Cooling blades of turbine rotor |
| CN101025091A (en) * | 2006-02-24 | 2007-08-29 | 通用电气公司 | Bucket platform cooling circuit and method |
| CN203547803U (en) * | 2013-12-04 | 2014-04-16 | 中航商用航空发动机有限责任公司 | Turbine cooling blade with impacting bush |
| US20160290139A1 (en) * | 2013-11-25 | 2016-10-06 | Brooks E. Snyder | Gas turbine engine component cooling passage turbulator |
| CN209604093U (en) * | 2018-12-26 | 2019-11-08 | 苏州大学 | A kind of turbine stator vane and turbine stator vane cooling structure |
-
2018
- 2018-12-26 CN CN201811598080.XA patent/CN109763864A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2098556U (en) * | 1991-06-01 | 1992-03-11 | 西安交通大学 | Cooling blades of turbine rotor |
| CN101025091A (en) * | 2006-02-24 | 2007-08-29 | 通用电气公司 | Bucket platform cooling circuit and method |
| US20160290139A1 (en) * | 2013-11-25 | 2016-10-06 | Brooks E. Snyder | Gas turbine engine component cooling passage turbulator |
| CN203547803U (en) * | 2013-12-04 | 2014-04-16 | 中航商用航空发动机有限责任公司 | Turbine cooling blade with impacting bush |
| CN209604093U (en) * | 2018-12-26 | 2019-11-08 | 苏州大学 | A kind of turbine stator vane and turbine stator vane cooling structure |
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