CN203867627U - Air film cooling component for gas turbine - Google Patents
Air film cooling component for gas turbine Download PDFInfo
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- CN203867627U CN203867627U CN201420142173.2U CN201420142173U CN203867627U CN 203867627 U CN203867627 U CN 203867627U CN 201420142173 U CN201420142173 U CN 201420142173U CN 203867627 U CN203867627 U CN 203867627U
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- air film
- hole
- cooling
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- film hole
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- 238000001816 cooling Methods 0.000 title claims abstract description 62
- 230000003014 reinforcing effect Effects 0.000 claims description 5
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 238000012986 modification Methods 0.000 description 13
- 230000004048 modification Effects 0.000 description 13
- 238000005516 engineering process Methods 0.000 description 5
- 150000001875 compounds Chemical class 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000010304 firing Methods 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000003321 amplification Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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Abstract
An air film cooling component for a gas turbine comprises a high-temperature side surface, a low-temperature side surface and an air film cooling structure arranged between the high-temperature side surface and the low-temperature side surface. The air film cooling structure comprises an air film gap and at least one air film hole, wherein the air film gap is formed in the high-temperature side surface, and the air film hole corresponds to the air film gap. The air film gap is composed of a flow guiding portion and a cold air cavity. The flow guiding portion is defined by a baffle plate and a lip opening, and an airflow channel extending in the direction forming a certain angle with the axis direction of the air film hole is formed. By the use of the air film cooling component, a more uniform cooled air film can be provided, and the structural strength of the air film cooling component cannot be excessively affected.
Description
Technical field
The utility model relates to a kind of air film cooling-part for gas turbine, and wherein, this air film cooling-part carrys out cooling its high temperature side by air film cooling technology.Especially, the related gas turbine of the utility model is aeroengine.
Background technique
What in aeroengine, conventionally adopt at present is gas turbine, and it comprises gas compressor, firing chamber, turbine and jet pipe.Along with the development of aero engine technology, the pressure ratio of its gas compressor significantly improves, and the out temperature of firing chamber also significantly improves.Wherein, the parts such as the firing chamber in gas turbine, turbine blade, turbine listrium need be in the face of the operating temperature day by day improving.For reply gas turbine operating temperature improves the problem of bringing, conventionally from two aspects, consider: the better material of first exploitation resistance to heat, it two is cooling capacities of strengthening heating part place.
At present, slow to thering is the development process of material of better resistance to heat, but aspect the exploitation of cooling technology, but obtaining development fast.To in parts cooling, need to guarantee to parts cooling evenly and fully.If cooling insufficient to parts can produce thermal stress on these parts.Cyclic thermal stres can cause such as parts generation thermal fatigues such as turbine blades for a long time, and then causes unit failure.
In numerous cooling technologies, air film cooling technology is applied to the cooling of each heating part in gas turbine more and more.In simple terms; air film is cooling is that more than one discrete hole is set on the parts in hot environment; from the low temperature side of these parts, introduce cooling working medium or jet; make this cooling working medium or jet through discrete hole, be ejected into the high temperature side of these parts; and form air film on the surface of high temperature side, thereby the surface of the incident area of jet and downstream area thereof is formed to protective film.
But, air film is cooling can not guarantee cooling effect completely uniformly.Specifically, what in air film cooling structure, adopt is discrete hole, and cooling blast flows into the high temperature side of parts through this discrete hole, and therefore, each source of the gas that forms air film is discrete distribution.Conventionally, near in the region of discrete hole, air film temperature is relatively low, and in region between adjacent discrete hole, air film temperature will be relatively high.Also someone proposes discrete air film hole to be modified as air film seam, to form the air film of continuous covering, thereby improves the even problem of air film inhomogeneous cooling.But, if form air film seam, needing to remove more material, this will exert an influence to the intensity of air film cooling-part.
Model utility content
Therefore, the purpose of this utility model is to provide a kind of air film cooling-part, and it is more even that the Film Cooling structure in this air film cooling-part can make air film distribute, and to guarantee cooling effectiveness, can guarantee again the structural strength of air film cooling-part self simultaneously.
Above-mentioned purpose of the present utility model realizes by a kind of air film cooling-part for gas turbine.This air film cooling-part comprises high temperature side surface, low temperature side is surperficial and be arranged on high temperature side surface and low temperature side surface between air film cooling structure, cooling-air can flow to high temperature side surface from low temperature side surface through air film cooling structure, form cooling air film, air film cooling structure comprises: at least one air film seam, air film seam is arranged on high temperature side surface, and form by the diversion division on contiguous high temperature side surface with away from the cold air cavity on high temperature side surface, cold air cavity is connected with diversion division; Wherein, each in stitching with at least one air film is provided with at least one air film hole accordingly, and air film hole extends to the bottom surface of air film seam from low temperature side surface, and is connected with cold air cavity; Wherein, diversion division is limited and is formed by deflection plate and lip, the air-flow path that the axial direction of formation and air film hole extends angularly.
By the above-mentioned air film cooling-part with air film cooling structure, first the cooling-air flowing out from discrete air film hole enters cold air cavity, in cold air cavity, fully mix, and then flow out air film seam through diversion division guiding, can obtain thus the cooling air film that area is wider, be more evenly distributed.Meanwhile, the combination of air film seam and air film hole can guarantee that the structural strength of parts is not a greater impact.
In above-mentioned air film cooling structure, the needs that distribute according to cooling-air, air film hole can be at least one in circular hole, elliptical aperture and square hole.
Or air film hole entrance that can air film hole is set to circle, the air film hole outlet of air film hole is set to square.Thus, obtain the air film hole of compound shape.
Preferably, each in stitching with at least one air film is provided with at least two air film holes accordingly, air film hole is arranged along the line of arranging, wherein, hole pitch between two adjacent air film holes meets following relation: d >=2.5R, wherein, d is the hole pitch between adjacent two air film holes, and R is from the center of the air film hole entrance of air film hole to the distance of arranging line and the intersection point of air film hole entrance.
Each in stitching with at least one air film is provided with in the situation of at least two air film holes accordingly, and air film hole is arranged along the line of arranging, and this line of arranging can be at least one in straight line, camber line, parabola.
Preferably, at least one place in the air film hole entrance of air film hole and the outlet of the air film hole of air film hole is processed with rounding or chamfering.Thus, can prevent that cooling-air from blocking at air film hole entrance and exit place, avoids consequent flow loss.
Preferably, the axial direction angulation of the direction of the air-flow path of diversion division and air film hole is between 45 °～90 °.
Preferably, the structure of air film seam meets at least one in following relation:
0.5S≤a*L≤2S, wherein, a is the perpendicular distance that lip is left at the tip of deflection plate; L is the length of air film seam; S stitches the gross area of the air film hole entrance of the air film hole being connected with same air film; And
M >=R, wherein, m is from the tip of deflection plate to the perpendicular distance of the central axis of air film hole, R is from the center of the air film hole entrance of air film hole to the distance of arranging line and the intersection point of air film hole entrance of air film hole.
According to the distribution situation of the high temperature gas flow of high temperature side surface, the tip of deflection plate and the perpendicular distance between lip can be along the bearing of trends of the line of arranging of air film hole and are changed.
Preferably, on low temperature side surface, be provided with at least one reinforcing part.By this reinforcing part, can further guarantee the structural strength of air film cooling-part.
The air film cooling-part with the above structure can be at least one in chamber wall, turbine blade and turbine listrium.
Accompanying drawing explanation
Fig. 1 shows the plan view of air film cooling-part of the present utility model, and this air film cooling-part is specially turbine blade.
Fig. 2 shows the detailed perspective of the part C of the air film cooling-part shown in Fig. 1.
Fig. 3 is the sectional view obtaining along the line A-A in Fig. 2.
Fig. 4 is the sectional view obtaining along the line B-B in Fig. 3.
Fig. 5 schematically shows a kind of layout of the air film hole in air film cooling-part of the present utility model.
Fig. 6 schematically shows the another kind of layout of the air film hole in air film cooling-part of the present utility model.
Fig. 7 shows the stereogram of the first modification mode of execution in air film cooling-part of the present utility model.
Fig. 8 shows the stereogram of the second modification mode of execution in air film cooling-part of the present utility model.
Fig. 9 shows the stereogram of the 3rd modification mode of execution in air film cooling-part of the present utility model.
Figure 10 shows the stereogram of the 4th modification mode of execution in air film cooling-part of the present utility model.
Embodiment
Below in conjunction with accompanying drawing, embodiment of the present utility model is elaborated.Should understand, shown in accompanying drawing is only preferred embodiment of the present utility model, and it does not form the restriction to scope of the present utility model.Those skilled in the art can carry out various apparent modifications, modification, equivalence replacement to the utility model on embodiment's shown in the drawings basis, within these all drop on protection domain of the present utility model.
In Fig. 1 with turbine blade for having exemplified air film cooling-part 1 of the present utility model.Although be turbine blade shown in this, but should understand, air film cooling-part of the present utility model can be also the parts that chamber wall, turbine listrium of gas turbine etc. worked under hot environment, and it has the cooling structure identical with the air film cooling structure that will describe in detail below.
As shown in Figure 1, air film cooling-part 1 is hollow structure, comprising several cooling chambers 2.On the surface of air film cooling-part 1, be provided with a plurality of air film cooling structures 3, this air film cooling structure is communicated with cooling chamber 2 with the high temperature side surface of air film cooling-part 1, cooling-air flows to this high temperature side surface through air film cooling structure 3 from cooling chamber 2, to form cooling air film.
The amplification stereogram of part C in Fig. 1 has been shown, comprising air film cooling structure 3 in Fig. 2.As shown in Figure 2, air film cooling structure 3 comprises air film hole 51 and air film seam 52, and wherein, each air film seam 52 is connected with a plurality of air film holes.Specifically, on the high temperature side surface 11 of air film cooling-part 1, offer air film seam 52, and a plurality of air film holes 51 are from the low temperature side surface 12(of air film cooling-part 1 towards the surface of cooling chamber 2) extend to the bottom surface of air film seam 52 always, and be connected with air film seam 52.Air film seam 52 is comprised of cold air cavity 53 and diversion division 54.
As shown in the sectional view in Fig. 3, diversion division 54 contiguous high temperature side surfaces 11, and limit and form by deflection plate 541 and lip 542, form the air-flow path angled with the axial direction of air film hole 51.Preferably, the air-flow path of diversion division 54 towards and the central axis of air film hole 51 between angle theta between 45 °～90 °.
The working principle of air film cooling structure 3 of the present utility model is described below with reference to Fig. 3 and 4.As shown in Figure 3, the flow through high temperature side surface 11 of air film cooling-part 1 of high temperature gas flow 20, heating high temperature side surface 11.Air film hole entrance 501 from the cooled gas 21 of cooling chamber 2 from low temperature side surface 12 flows into, and exports in the cold air cavity 53 that 502 places flow into air films seam 52 at air film hole.In cold air cavity 53, cooled gas from different air film holes fully mixes, and then flows in the formed diversion division 54 of deflection plate 541 and lip 542, and flows out from diversion division with the form of continuous air film, thereby on high temperature side surface 11, form continuous air film 22, as shown in Figure 4.
Wherein, when cooled gas flows to diversion division 54 from cold air cavity 53, cooled gas 21 can impact deflection plate 541, thereby form, impacts cooling effect.This can further improve the cooling effect of air film cooling structure 3.
For the structure of air film seam 52, it preferably meets following relation:
0.5S≤a*L≤2S
Wherein, a is the perpendicular distance that lip 542 is left at the tip of deflection plate 541, as shown in Figure 3; L is the length of air film seam; S stitches the gross area of the air film hole entrance 501 of the air film hole 51 being connected with same air film.Can know, above a*L is the discharge area of air film seam 52.
In the air film cooling structure 3 shown in Fig. 2, air film hole 51 is circular hole, and therefore the gross area of above air film hole entrance 501 can be expressed as S=n π R
2.Wherein, R is that line 4(is arranged as shown in Fig. 2,5 and 6 to air film hole in the center of air film hole entrance) and the intersection point of air film hole entrance between distance, in the situation of circular hole, be the radius of air film hole entrance 501; N is the quantity of air film hole.
Preferably, the rear baffling segment length m of deflection plate 541 is more than or equal to the size R in air film hole entrance 501.At this, rear baffling segment length m refers to from the tip of deflection plate 541 to the perpendicular distance of the central axis of air film hole.
By making m be more than or equal to R, can strengthen shock effect, make the guide flow path of cooled gas longer simultaneously.
A kind of setting type of air film hole 51 has been shown in Fig. 5.Wherein, a plurality of air film holes 51 are arranged along the line 4 of arranging linearly.Hole pitch between adjacent two air film holes 51 (being the distance between Liang Gekong center) d >=2.5R.
Fig. 6 shows the schematic diagram of another setting type of air film hole, wherein visible, and the line 4 of arranging of air film hole is the form of camber line.Hole pitch between adjacent air film hole 51, the perpendicular distance between the center of two air film holes still preferably meets this relation of d >=2.5R.
Except the air film hole setting type shown in Fig. 5 and Fig. 6, according to the temperature distribution of the high temperature gas flow of incoming flow, the line 4 of arranging of air film hole 51 also can be the line style of other forms such as parabola.
Except above disclosed concrete structure, also can carry out following modification to the air film cooling structure 3 in air film cooling-part 1.
The first modification mode of execution of air film cooling-part has been shown in Fig. 7.Wherein, the air film cooling structure 3 shown in air film cooling structure and Fig. 2～4 is basic identical.Its difference is only, the cross section of the air film hole 51 of the air film cooling structure shown in Fig. 7 is oval.
The second modification mode of execution of air film cooling-part has been shown in Fig. 8.Wherein, air film cooling structure is only with the difference of disclosed air film cooling structure before, and the cross section of the air film hole 51 of the air film cooling structure shown in Fig. 8 is square.
Fig. 9 shows the 3rd modification mode of execution of air film cooling-part, and wherein, air film hole 51 is compound shape.Specifically, as shown in Figure 9, the air film hole entrance 501 of this air film hole is circular, and its air film hole outlet 502 is square.
Air film hole also can be taked other suitable shape.
In the 4th modification mode of execution of the air film cooling-part shown in Figure 10, on the low temperature side surface 12 of these parts, reinforcing part 13 is additionally set, further to strengthen the structural strength of air film cooling-part.This reinforcing part 13 can be for example form of raised line.
Except above-described modification mode of execution, also can carry out following modification to the utility model:
Preferably, according to the temperature distribution of the high temperature gas flow of incoming flow, the perpendicular distance a between the tip of deflection plate 541 and lip 542 can change along the bearing of trend of the line 4 of arranging.Like this, can provide different cooled gas flows according to zones of different temperature separately.
Preferably, in order to prevent that air-flow from exporting 502 places' obstructions at air film hole entrance 501 and air film hole, cause the loss of air-flow, can carry out chamfering or rounding processing to air film hole entrance 501 and air film hole outlet 502.
In addition, air film hole 51 can be arranged to from air film hole entrance 501 to air film hole, export 502 areas increases gradually.
In above disclosed mode of execution, air film hole can be a kind of in the hole of circular hole, elliptical aperture, square hole and compound shape.According to actual demand, a plurality of air film holes that are connected with air film seam also can comprise two or more in the hole of circular hole, elliptical aperture, square hole and compound shape simultaneously.
Claims (11)
1. the air film cooling-part for gas turbine, described air film cooling-part comprises high temperature side surface, low temperature side is surperficial and be arranged on the air film cooling structure between described high temperature side surface and described low temperature side surface, cooling-air can flow to described high temperature side surface from described low temperature side surface through described air film cooling structure, form cooling air film, it is characterized in that, described air film cooling structure comprises:
At least one air film seam, described air film seam is arranged on described high temperature side surface, and forms by the diversion division on contiguous described high temperature side surface with away from the cold air cavity on described high temperature side surface, and described cold air cavity is connected with described diversion division;
Wherein, each in stitching with described at least one air film is provided with at least one air film hole accordingly, and described air film hole extends to the bottom surface of described air film seam from described low temperature side surface, and is connected with described cold air cavity;
Wherein, described diversion division is limited and is formed by deflection plate and lip, the air-flow path that the axial direction of formation and described air film hole extends angularly.
2. the air film cooling-part for gas turbine as claimed in claim 1, is characterized in that, described air film hole is at least one in circular hole, elliptical aperture and square hole.
3. the air film cooling-part for gas turbine as claimed in claim 1, is characterized in that, the air film hole entrance of described air film hole is circular, and the air film hole outlet of described air film hole is for square.
4. the air film cooling-part for gas turbine as claimed in claim 1, it is characterized in that, each in stitching with described at least one air film is provided with at least two described air film holes accordingly, described air film hole is arranged along the line of arranging, wherein, hole pitch between two adjacent described air film holes meets following relation: d >=2.5R, wherein, d is the hole pitch between adjacent two described air film holes, and R is from the center of the air film hole entrance of described air film hole to described distance of arranging line and the intersection point of described air film hole entrance.
5. the air film cooling-part for gas turbine as claimed in claim 1, it is characterized in that, each in stitching with described at least one air film is provided with at least two described air film holes accordingly, described air film hole is arranged along the line of arranging, wherein, the line of arranging described in is at least one in straight line, camber line, parabola.
6. the air film cooling-part for gas turbine as claimed in claim 1, is characterized in that, at least one place in the air film hole entrance of described air film hole and the outlet of the air film hole of described air film hole is processed with rounding or chamfering.
7. the air film cooling-part for gas turbine as claimed in claim 1, is characterized in that, described angle is between 45 °～90 °.
8. the air film cooling-part for gas turbine as claimed in claim 1, is characterized in that, the structure of described air film seam meets at least one in following relation:
0.5S≤a*L≤2S, wherein, a is the perpendicular distance that described lip is left at the tip of described deflection plate; L is the length of described air film seam; S stitches the gross area of the air film hole entrance of the described air film hole being connected with same described air film; And
M >=R, wherein, m is from the tip of described deflection plate to the perpendicular distance of the central axis of described air film hole, R is from the center of the air film hole entrance of described air film hole to the distance of arranging line and the intersection point of described air film hole entrance of described air film hole.
9. the air film cooling-part for gas turbine as claimed in claim 1, is characterized in that, the perpendicular distance between the tip of described deflection plate and described lip is along the bearing of trend of the line of arranging of described air film hole and change.
10. the air film cooling-part for gas turbine as claimed in claim 1, is characterized in that, on described low temperature side surface, is provided with at least one reinforcing part.
11. air film cooling-parts for gas turbine as described in any one in claim 1～10, is characterized in that, described air film cooling-part is at least one in chamber wall, turbine blade and turbine listrium.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420142173.2U CN203867627U (en) | 2014-03-27 | 2014-03-27 | Air film cooling component for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420142173.2U CN203867627U (en) | 2014-03-27 | 2014-03-27 | Air film cooling component for gas turbine |
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| CN203867627U true CN203867627U (en) | 2014-10-08 |
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| CN201420142173.2U Expired - Lifetime CN203867627U (en) | 2014-03-27 | 2014-03-27 | Air film cooling component for gas turbine |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104791848A (en) * | 2014-11-25 | 2015-07-22 | 西北工业大学 | Combustion chamber flame cylinder wall face with blade grid channel multi-inclined-hole cooling manner adopted |
| CN108223019A (en) * | 2017-12-20 | 2018-06-29 | 中国科学院宁波材料技术与工程研究所 | A kind of hollow blade and its manufacturing method and application |
| CN108590777A (en) * | 2018-06-13 | 2018-09-28 | 中国科学院宁波材料技术与工程研究所 | A kind of recurring structure of the continuous air film of matrix surface |
| CN108731030A (en) * | 2018-08-10 | 2018-11-02 | 宁波大艾激光科技有限公司 | A kind of combustion chamber with compound special-shaped groove gaseous film control structure |
| CN108843404A (en) * | 2018-08-10 | 2018-11-20 | 中国科学院宁波材料技术与工程研究所 | A kind of turbo blade and preparation method thereof with compound special-shaped groove gaseous film control structure |
| CN108843403A (en) * | 2018-06-13 | 2018-11-20 | 中国科学院宁波材料技术与工程研究所 | A method of continuous air film is generated in matrix surface |
| CN108869099A (en) * | 2018-06-01 | 2018-11-23 | 北京航空航天大学 | Gaseous film control structure, liquid-propellant rocket engine and its gaseous film control test method |
| CN111578310A (en) * | 2020-04-30 | 2020-08-25 | 南京理工大学 | Air film cooling hole structure for turboshaft engine |
| WO2022227583A1 (en) * | 2021-04-28 | 2022-11-03 | 浙江意动科技股份有限公司 | Air film hole turbine blade having bending angle |
| RU2787678C2 (en) * | 2018-08-10 | 2023-01-11 | Нинбо Инститьют Оф Мэтириэлз Текнолоджи Энд Энжиниэринг Чайниз Экэдэми Оф Сайэнсэз | Turbine blade with structure for gas-film cooling with composite groove of irregular shape and its manufacturing method |
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- 2014-03-27 CN CN201420142173.2U patent/CN203867627U/en not_active Expired - Lifetime
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| CN104791848A (en) * | 2014-11-25 | 2015-07-22 | 西北工业大学 | Combustion chamber flame cylinder wall face with blade grid channel multi-inclined-hole cooling manner adopted |
| CN108223019A (en) * | 2017-12-20 | 2018-06-29 | 中国科学院宁波材料技术与工程研究所 | A kind of hollow blade and its manufacturing method and application |
| CN108869099A (en) * | 2018-06-01 | 2018-11-23 | 北京航空航天大学 | Gaseous film control structure, liquid-propellant rocket engine and its gaseous film control test method |
| CN108590777A (en) * | 2018-06-13 | 2018-09-28 | 中国科学院宁波材料技术与工程研究所 | A kind of recurring structure of the continuous air film of matrix surface |
| WO2019237720A1 (en) * | 2018-06-13 | 2019-12-19 | 中国科学院宁波材料技术与工程研究所 | Method for producing continuous gas film on surface of base body |
| CN108843403A (en) * | 2018-06-13 | 2018-11-20 | 中国科学院宁波材料技术与工程研究所 | A method of continuous air film is generated in matrix surface |
| WO2020029531A1 (en) * | 2018-08-10 | 2020-02-13 | 中国科学院宁波材料技术与工程研究所 | Turbine blade having composite specially-shaped slotted gas film cooling structure and manufacturing method thereof |
| CN108843404A (en) * | 2018-08-10 | 2018-11-20 | 中国科学院宁波材料技术与工程研究所 | A kind of turbo blade and preparation method thereof with compound special-shaped groove gaseous film control structure |
| CN108731030A (en) * | 2018-08-10 | 2018-11-02 | 宁波大艾激光科技有限公司 | A kind of combustion chamber with compound special-shaped groove gaseous film control structure |
| JP2021535312A (en) * | 2018-08-10 | 2021-12-16 | 中国科学院▲寧▼波材料技▲術▼▲与▼工程研究所Ningbo Institute Of Materials Technology & Engineering, Chinese Academy Of Sciences | Turbine blade having a gas film cooling structure with a composite irregular groove and its manufacturing method |
| US11352888B2 (en) | 2018-08-10 | 2022-06-07 | Ningbo Institute Of Materials Technology & Engineering, Chinese Academy Of Sciences | Turbine blade having gas film cooling structure with a composite irregular groove and a method of manufacturing the same |
| RU2787678C2 (en) * | 2018-08-10 | 2023-01-11 | Нинбо Инститьют Оф Мэтириэлз Текнолоджи Энд Энжиниэринг Чайниз Экэдэми Оф Сайэнсэз | Turbine blade with structure for gas-film cooling with composite groove of irregular shape and its manufacturing method |
| JP7268135B2 (en) | 2018-08-10 | 2023-05-02 | 中国科学院▲寧▼波材料技▲術▼▲与▼工程研究所 | Turbine blade having gas film cooling structure with compound profile groove and method for manufacturing the same |
| CN108731030B (en) * | 2018-08-10 | 2024-02-13 | 宁波大艾激光科技有限公司 | Combustion chamber with composite special-shaped groove air film cooling structure |
| CN111578310A (en) * | 2020-04-30 | 2020-08-25 | 南京理工大学 | Air film cooling hole structure for turboshaft engine |
| WO2022227583A1 (en) * | 2021-04-28 | 2022-11-03 | 浙江意动科技股份有限公司 | Air film hole turbine blade having bending angle |
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| C14 | Grant of patent or utility model | ||
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: 201108 Shanghai city Minhang District Lotus Road No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20141008 |