CN103452595A - Novel air film hole with improved cooling efficiency - Google Patents
Novel air film hole with improved cooling efficiency Download PDFInfo
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- CN103452595A CN103452595A CN2013104404090A CN201310440409A CN103452595A CN 103452595 A CN103452595 A CN 103452595A CN 2013104404090 A CN2013104404090 A CN 2013104404090A CN 201310440409 A CN201310440409 A CN 201310440409A CN 103452595 A CN103452595 A CN 103452595A
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- 238000001816 cooling Methods 0.000 title claims abstract description 84
- 238000007664 blowing Methods 0.000 claims abstract description 13
- 238000011144 upstream manufacturing Methods 0.000 claims description 8
- 238000000034 method Methods 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 abstract description 3
- 230000002349 favourable effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 14
- 239000007789 gas Substances 0.000 description 11
- 239000002737 fuel gas Substances 0.000 description 7
- 230000007423 decrease Effects 0.000 description 4
- 238000011160 research Methods 0.000 description 4
- 230000001464 adherent effect Effects 0.000 description 3
- 210000005056 cell body Anatomy 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000001629 suppression Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 230000029058 respiratory gaseous exchange Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a novel cooling hole capable of improving the cooling efficiency of an air film of a turbine engine. The novel cooling hole structurally comprises conical holes and a rectangular transverse groove. The rectangular transverse groove is formed in the conical holes along the direction perpendicular to the flowing direction of cold air. An included angle between the axis of each hole and a plane ranges from 10 degrees to 40 degrees, the conical holes are machined on the basis of cylindrical holes, an orifice of each conical hole is a conical opening with an opening angle which ranges from 10 degrees to 20 degrees, and the depth of the transverse groove ranges from 0.5D to 1.0D. Compared with conventional cylindrical air film hole structures, the novel cooling hole has the advantages that the exit sectional area is increased by the conical nozzle holes, so that the main flow penetrating ability of jet flow is reduced, reverse vortex pairs around the nozzle holes can be effectively suppressed, and accordingly the cooling efficiency can be improved; vertical fixed walls of the transverse groove at the lower edges of the conical holes can stop cooling air flow from flowing, so that parts of the cooling air flow flow to two sides of the novel cooling hole, and the novel cooling hole is favorable for transversely diffusing the cooling air flow; the cooling efficiency of the novel cooling hole can be improved by about 300% as compared with the traditional cylindrical air film hole under the condition of a certain blowing ratio.
Description
Technical field
The present invention relates to the air film cooling technology field in turbine power plant, be a kind of Novel air fenestra that can improve turbine blade of gas turbine and combustion chamber wall surface cooling effectiveness, be applicable to the requirement of High Performance Aeroengine of new generation to the high-temperature component cooling performance.
Background technique
The high speed development of modern aeroengine improves constantly turbine inlet gas temperature, thereby increases the weight of the heat load of blade, causes the blade material hydraulic performance decline, affects the safe operation of motor.According to U.S.'s authoritative department statistics, the fault of aeroengine has and surpasses 60% and appear at high temperature position, and the trend of continuous rising arranged, the life-span of some engine hot parts of China generally only has hundreds of hour, and the material cost of high-temperature component and processing charges are very expensive, the economic loss of bringing thus is very serious.Therefore, must adopt effective cooling method to be protected turbine blade, make it avoid high temperature corrosion or damage.
In numerous cooling technologies, air film is cooling all to be widely used in combustion gas in modern age wheel air breathing engine, pressed engine main combustion chamber, guide vane, working blade, leaf grating sidewall and tail pipe burner.The firing chamber of rocket motor and jet pipe and supersonic wing all can adopt air film cooling.It is by offering the line of rabbet joint or aperture on the high-temperature component surface, form by cooling medium with transverse jet is injected in main flow, under the effect of the pressure of main flow and frictional force, the jet bending also is covered in the high-temperature component surface, the cold air film that formation temperature is lower, thus high-temperature component is played to heat insulation and cooling effect.
Film Cooling mainly is subject to the geometrical construction (comprising the spray angle, pore size, Kong Changyu aperture ratio, the spacing in hole, the shape of hole exits of air film hole etc.) of air film hole, the geometric parameter of blade and the factors such as the aerodynamic parameter impact of air film hole.Much research shows, air film jet exit place velocity distribution is very inhomogeneous, the flow field structure complexity, and different shaped film-holes are on the attached wall of cooling air film, horizontal cover width, overlay length and the cooling effect in downstream, aperture is had to significant impact longitudinally.With cylindrical hole, compare, the air film hole export expansion can reduce the exit momentum of cold air at air film hole, weakens the blending degree of cold air and combustion gas, improves the attaching of cold air at wall, has better heat insulation cooling effect.Especially height blowing than the time expanded bore can suppress to some extent the generation of counter-rotating vortices pair, can provide better heat protection to the air film cooling surface.Expansion shape air film hole can obtain than conventional cylindrical hole cooling effect preferably, but find by the analysis to speed vector figure in hole, still have obvious flow separation and irreqularity in air film hole, and simple expansion shape hole does not utilize cold air fully, and may bring larger aerodynamic loss.
In conventional discrete holes air film is cooling, zone between Kong Yukong is cooling weakness zone, research is found to offer a translot that certain depth and width are arranged in the air film hole outlet port along the direction vertical with cold air flow, can make the transverse distribution of air film more even, and significantly improve the be cooled cooling effect of wall of groove downstream.Compare with other cooling structure, have simple in structurely with the air film of transverse groove is cooling, be easy to processing, characteristics that air consumption is few.But current research focuses mostly on and opens transverse groove in cylindrical air film hole outlet port, and unrealized by expanded bore with open transverse groove and effectively combine.The present invention, through meticulous design and research, makes the cooling effectiveness of this Novel air fenestra under difference blowing ratio all higher than simple expanded bore and grooved bore, and is easy to processing,
It is a kind of film cooling holes type that practical prospect is arranged very much.
Summary of the invention
The purpose of this invention is to provide a kind of New Gas Film hole structure that improves cooling effectiveness, this hole shape is more remarkable to the improvement of horizontal cooling effectiveness between downstream air film hole centerline cooling effectiveness and two air film holes, and the nonuniformity of cooling film overcast is reduced.
For achieving the above object, technical solution of the present invention is:
The present invention includes the conical air film hole 1 be positioned on flat board, and the rectangle translot 2 of opening along the direction vertical with cold air flow on conical air film hole 1, it is characterized in that: Novel air fenestra axially bored line and plane are in tilted layout, cylindrical hole is processed into to the cone shaped opening of certain aperture subtended angle, has a transverse groove 2 above cone shaped opening.
The Novel air fenestra is for opening the embedded conical bore of translot, and hole row be comprised of 3 holes, Kong Changyu aperture ratio L/D=4～5, distance between Kong Yukong is 3.0D～5.0D, the air film hole height is 2.5D～3.5D, and the scope of blowing ratio M is 0.5～2.0, is applicable to any surface along pressure gradient.
Air film hole axis and plane are in tilted layout, and the scope of the angle α of axially bored line and flow direction is 10 °～40 °.
Round taper hole is to process on the basis of cylindrical hole, the cross section of air film hole in the cold air ingress is circular, upstream from about 2/3 place of air film hole entrance height is the cone shaped opening that a subtended angle is 10 °～20 °, and downstream is one to be highly the vertical Gu Bi of 0.5D～1.0D.
Conical air film hole opening top has transverse groove, and the vertical Gu Bi of translot upstream and downstream and conical air film hole opening distance are 1.0D～1.5D, and the transverse groove degree of depth is 0.5D～1.0D.
The present invention, owing to being to open the embedded conical expansion of translot hole, therefore makes the lateral separation between air film hole shorten, the air-flow of adjacent two holes ejection, and along with the expansion to both sides, air-flow mixes, and has strengthened cooling effect.And because axially bored line and flow direction tilt, caused the more extensively expansion of stronger lateral momentum and jet, make along transversely eject stream continuously, cold air broad covered area, thereby produced higher horizontal cooling effectiveness.In addition, effective combination due to conical expansion hole and translot, mobile in this Novel air fenestra of cold air jet had sufficient development, the segregation phenomenon of cold air flow almost disappears, flow more regular, because it has special fluidic architecture, make the uniform high velocity air of development in hole directly overlay the wall that is cooled after the effluent gases fenestra, and near the suitable pressure gradient formed aperture has been eliminated the separation that jet forms in the ingress, hole, therefore can obtain better cooling effect.
The accompanying drawing explanation
Fig. 1 is Novel air fenestra side view of the present invention.
Fig. 2 is Novel air fenestra plan view of the present invention.
Fig. 3 is the speed vector figures of different air film holes in blowing ratio M=1.0 o'clock, wherein:
The speed vector figure that Fig. 3 (a) is cylindrical hole.
Fig. 3 (b) is Novel hole speed vector figure of the present invention.
The side view that Fig. 4 is one embodiment of the present of invention.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
With reference to Fig. 1, shown in 2, for a kind of side view and plan view that improves the gas film cooling efficiency Novel hole of the present invention, comprise conical bore 1, transverse groove 2 and minimum unit body (Novel hole) 3.The angle α of the axially bored line of Novel hole 3 of the present invention and flow direction is between 10 °～40 °, the angle β of cone shaped opening and axially bored line is between 10 °～20 °, upstream is one highly for h1(0.5D～1.0D) vertical Gu Bi, air film hole 3 height are expressed as 2.5D～3.5D with H, transverse groove 2 degree of depth h are between 0.5D～1.0D, the vertical Gu Bi of translot upstream and downstream and conical air film hole 1 opening apart from w between 1.0D～1.5D, translot 2 width are W, and the distance P between Kong Yukong is between 3.0D～5.0D.Several main flow directions are used respectively coordinate X, Y, and Z illustrates, and X is for flowing to, and Y be horizontal, and Z is for radially.High-temperature fuel gas 5 flows through from hot side surface 4, and the air film hole ingress that cooling blast 6 is D from diameter enters, and through conical air film hole 1, from translot 2, flows out.
Add a transverse groove 2 that certain depth and width are arranged at conical air film hole 1 opening, make cooling blast 6 after the conical air film hole 1 of outflow enters transverse groove 2, the jet circulation area further enlarges, the momentum decrease, Film Cooling also decreases to the vertical penetrating power of main flow, it is larger that the diffusion that jet itself is mobile and jet are subject to the main flow suppression downward to it in flowing into transverse groove 2, oppositely the intensity of vortex pair has been subject to inhibition to some extent, has strengthened the cooling effect of wall.
The degree of depth h of transverse groove 2: under certain blowing ratio M, the large young pathbreaker of transverse groove 2 degree of depth affects Film Cooling to a great extent, and value should be between 0.5D～1.0D.For shallow slot, cooling blast 6 with enter shallow slot before high-temperature fuel gas 5 mixes, will be full of very soon whole cell body, expand to both sides and mix from the air-flow of adjacent 2 spray orifices ejection, caused stronger lateral momentum, thus along the exhibition to cooling effect better.For deep trouth, intensification due to transverse groove 2 degree of depth, after cooling blast 6 enters air film hole, at first spread in groove before with high-temperature fuel gas 5, not carrying out blending and formed very thin air-flow, cause the cooling effectiveness in transverse groove 2 higher, and it is poor at air film hole downstream cooling effect, its cooling effectiveness reduces along with the increase of blowing ratio, its reason is the increase along with the blowing ratio, the initial momentum of jet increases gradually, because transverse groove 2 degree of depth are darker, cause jet more concentrated when notch sprays, directly through boundary layer, enter main flow area after ejection, make the spreadability of cooling blast 6 poor, thereby cooling effectiveness is lower.
The width W of transverse groove 2: under certain blowing ratio M, the change width of transverse groove 2 has considerable influence to the average cooling effectiveness in air film hole downstream.For narrow groove, cooling blast 6 is when the effluent gases fenestra, the constraint effect of 3 pairs of cooling blasts 6 of air film hole is stronger, cooling blast 6 is less to the diffusing capacity of both sides, cooling blast 6 flows out with the form that comparatively restrains gathering, with high-temperature fuel gas 5 blending, cause the adherent property of cold airflow 6 poor, the cooling effectiveness in air film hole 3 downstreams is also lower.And for sipes, cooling blast 6 has expansion largely in the air film hole outlet port, reduced its momentum upwards sprayed, and causes the adherent property of cooling blast 6 better, cooling blast 6 is by the whole zone in coating gas fenestra 3 outlet downstreams, and the average cooling effectiveness in air film hole 3 downstreams is also higher.
Fig. 3 is the speed vector figures of different air film holes in blowing ratio M=1.0 o'clock, wherein, the speed vector figure that Fig. 3 (a) is cylindrical hole, Fig. 3 (b) is Novel hole 3 speed vector figures of the present invention.As can be seen from the figure, near the tangential stress produced due to the speed difference of main flow and jet cylindrical hole has generated all larger reverse vortex pairs of intensity and size, and oppositely the hot air flow that makes both sides that entrainments of vortex pair is doped in cold airflow, causes the cooling effect variation.Than cylindrical hole, the intensity of Novel hole 3 of the present invention reverse vortex pair on adiabatic wall weakens to some extent, this is at outflow cone shape hole opening and after entering cell body due to the cold air jet, jet circulation enlarged areas, make its momentum reduce, thereby the penetrating power that cooling blast 6 goes out to flow to high-temperature fuel gas 5 decreases, and cold air jet 6 is subject to high-temperature fuel gas 5 suppression downward to it after flowing into cell body, cause the intensity of reverse vortex pair to be suppressed, thereby can cover well wall after cold airflow 6 effluent gases fenestras 3, improved Film Cooling.
Below one embodiment of the present of invention.
Shown in Fig. 4, air film hole axis and plane are in tilted layout, the angle α of axially bored line and flow direction is taken as 30 °, D is 10mm, air film hole 3 is highly 3.0D, and the angle β of cone shaped opening and axially bored line gets 15 °, and the height h1 of the vertical Gu Bi in upstream is 0.5D, round taper hole 1 is conducive to enlarge the film overcast rate of downstream wall, and improves laterally average gas film cooling efficiency.The degree of depth of transverse groove 2 has a great impact Film Cooling, and deep trouth is when blowing ratio M is larger, and air film hole downstream cooling effect at a distance is poor, thus groove depth should not get too dark, get 0.75D here.Transverse groove 2 is wider, make the adherent property of cooling blast 6 better, cooling blast 6 is by the whole zone in coating gas fenestra 3 outlet downstreams, the average cooling effectiveness in air film hole 3 downstreams is also higher, therefore in the present embodiment, the vertical Gu Bi of translot upstream and downstream and conical air film hole 1 opening distance are 1.5D.High-temperature fuel gas 5 flows through from hot side surface 4, and the air film hole ingress that cooling blast 6 is D from diameter enters, and flows out from translot 2 through conical air film hole 1, thereby carries out effectively cooling to hot side surface 4.
Claims (5)
1. a Novel air fenestra that improves cooling effectiveness, comprise the conical air film hole 1 be positioned on flat board, and the rectangle translot 2 of opening along jet direction on conical air film hole, it is characterized in that: axially bored line and the plane of Novel air fenestra 3 are in tilted layout, cylindrical hole is processed into to the cone shaped opening of certain aperture subtended angle, above cone shaped opening, along the direction vertical with cold air flow, has a rectangle translot 2.
2. a kind of Novel air fenestra that improves cooling effectiveness according to claim 1, it is characterized in that, described Novel air fenestra 3 is for opening the embedded conical bore 1 of translot 2, hole row be comprised of 3 holes, Kong Changyu aperture ratio L/D=4～5, the distance between Kong Yukong is 3.0D～5.0D, air film hole 3 is highly 2.5D～3.5D, the scope of blowing ratio M is 0.5～2.0, is applicable to any surface along pressure gradient.
3. a kind of Novel air fenestra that improves cooling effectiveness according to claim 1, is characterized in that, air film hole axis and plane are in tilted layout, and the scope of the angle α of axially bored line and flow direction is 10 °～40 °.
4. a kind of Novel air fenestra that improves cooling effectiveness according to claim 1, it is characterized in that, round taper hole 1 is to process on the basis of cylindrical hole, the cross section of air film hole 3 in the cold air ingress is circular, from about 2/3 upstream, place of air film hole entrance height, it is the cone shaped opening that a subtended angle is 10 °～20 °, downstream is one to be highly the vertical Gu Bi of 0.5D～1.0D, thereby causes the remarkable increase of air film hole outlet cross-section area.
5. a kind of Novel air fenestra that improves cooling effectiveness according to claim 1, it is characterized in that, conical air film hole 1 opening top has a transverse groove 2, the distance of the vertical Gu Bi of translot upstream and downstream and conical air film hole 1 opening is 1.0D～1.5D, and transverse groove 2 degree of depth are 0.5D～1.0D.
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| CN2013104404090A CN103452595A (en) | 2013-09-25 | 2013-09-25 | Novel air film hole with improved cooling efficiency |
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| CN2013104404090A CN103452595A (en) | 2013-09-25 | 2013-09-25 | Novel air film hole with improved cooling efficiency |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106401654A (en) * | 2016-10-31 | 2017-02-15 | 中国科学院工程热物理研究所 | Disperse air film cooling hole structure |
| CN106640216A (en) * | 2017-01-05 | 2017-05-10 | 河北工业大学 | Air film cooling hole structure |
| CN106969872A (en) * | 2017-04-18 | 2017-07-21 | 北京航空航天大学 | A kind of pressure probe of use double-row hole gaseous film control |
| CN106996848A (en) * | 2017-04-18 | 2017-08-01 | 北京航空航天大学 | A kind of pressure probe of use single row of holes gaseous film control |
| CN109060152A (en) * | 2018-07-19 | 2018-12-21 | 中国航发沈阳发动机研究所 | A kind of thermocouple sensor for the test of combustor exit thermal field |
| CN109738193A (en) * | 2019-01-08 | 2019-05-10 | 哈尔滨电气股份有限公司 | Gas-turbine combustion chamber test measures segment structure with air-cooled type |
| CN111102600A (en) * | 2019-11-08 | 2020-05-05 | 南京航空航天大学 | Cooling structure for large-curvature small elbow pipe inside backflow combustion chamber of turboshaft engine |
| CN112443361A (en) * | 2020-11-04 | 2021-03-05 | 西北工业大学 | A reverse air film pore structure of pit for turbine blade |
| CN112901283A (en) * | 2021-03-04 | 2021-06-04 | 西安交通大学 | Multistage suction air film cooling hole structure of bat ray type bionic boss and pit structure |
| CN114151140A (en) * | 2021-11-25 | 2022-03-08 | 哈尔滨工程大学 | Air film cooling structure applied to turbine stationary blade |
| CN114165811A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Jet sleeve with cooling structure |
| CN114412580A (en) * | 2022-02-09 | 2022-04-29 | 北京全四维动力科技有限公司 | Turbine blade air film cooling structure and gas turbine adopting same |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106401654A (en) * | 2016-10-31 | 2017-02-15 | 中国科学院工程热物理研究所 | Disperse air film cooling hole structure |
| CN106640216A (en) * | 2017-01-05 | 2017-05-10 | 河北工业大学 | Air film cooling hole structure |
| CN106969872B (en) * | 2017-04-18 | 2020-01-10 | 北京航空航天大学 | Pressure probe adopting double-row-hole air film cooling |
| CN106969872A (en) * | 2017-04-18 | 2017-07-21 | 北京航空航天大学 | A kind of pressure probe of use double-row hole gaseous film control |
| CN106996848A (en) * | 2017-04-18 | 2017-08-01 | 北京航空航天大学 | A kind of pressure probe of use single row of holes gaseous film control |
| CN106996848B (en) * | 2017-04-18 | 2020-05-22 | 北京航空航天大学 | Pressure probe adopting single-row-hole air film cooling |
| CN109060152A (en) * | 2018-07-19 | 2018-12-21 | 中国航发沈阳发动机研究所 | A kind of thermocouple sensor for the test of combustor exit thermal field |
| CN109060152B (en) * | 2018-07-19 | 2020-10-09 | 中国航发沈阳发动机研究所 | Thermocouple sensor for testing outlet temperature field of combustion chamber |
| CN109738193A (en) * | 2019-01-08 | 2019-05-10 | 哈尔滨电气股份有限公司 | Gas-turbine combustion chamber test measures segment structure with air-cooled type |
| CN111102600A (en) * | 2019-11-08 | 2020-05-05 | 南京航空航天大学 | Cooling structure for large-curvature small elbow pipe inside backflow combustion chamber of turboshaft engine |
| CN111102600B (en) * | 2019-11-08 | 2023-10-13 | 南京航空航天大学 | Inside big camber of vortex shaft engine backward flow combustion chamber little return bend cooling structure |
| CN112443361A (en) * | 2020-11-04 | 2021-03-05 | 西北工业大学 | A reverse air film pore structure of pit for turbine blade |
| CN112901283A (en) * | 2021-03-04 | 2021-06-04 | 西安交通大学 | Multistage suction air film cooling hole structure of bat ray type bionic boss and pit structure |
| CN114165811A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Jet sleeve with cooling structure |
| CN114151140A (en) * | 2021-11-25 | 2022-03-08 | 哈尔滨工程大学 | Air film cooling structure applied to turbine stationary blade |
| CN114412580A (en) * | 2022-02-09 | 2022-04-29 | 北京全四维动力科技有限公司 | Turbine blade air film cooling structure and gas turbine adopting same |
| CN114412580B (en) * | 2022-02-09 | 2024-02-09 | 北京全四维动力科技有限公司 | Turbine blade air film cooling structure and gas turbine adopting same |
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Application publication date: 20131218 |