CN211715181U - Laminate cooling structure with slotted circular turbulence column - Google Patents
Laminate cooling structure with slotted circular turbulence column Download PDFInfo
- Publication number
- CN211715181U CN211715181U CN202020345598.9U CN202020345598U CN211715181U CN 211715181 U CN211715181 U CN 211715181U CN 202020345598 U CN202020345598 U CN 202020345598U CN 211715181 U CN211715181 U CN 211715181U
- Authority
- CN
- China
- Prior art keywords
- side plate
- slotted circular
- columns
- slotted
- column
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A laminated plate cooling structure with a slotted circular turbulence column relates to the cooling technology of a gas turbine and is used for cooling turbine blades of the gas turbine. Comprises an outer side plate, an inner side plate and a slotted circular turbulent flow column; the outer side plate is provided with an inclined gas film hole and is close to the gas side; the inner side plate is provided with an impact hole and is close to the cold air side; the slotted circular turbulence column is arranged in a cooling channel formed between the outer side plate and the inner side plate; the cooling gas firstly impacts the outer side plate through the impact holes, enters the cooling channel and is subjected to enhanced heat exchange with the turbulence columns, and then flows out along the air film holes of the outer side plate. When the slit inclination angle beta of the slotted circular turbulence column is 0 degrees, compared with a conventional laminate cooling system, the pressure loss can be reduced, the thermal uniformity of the laminate is improved, and the cooling efficiency of air flow is improved; when the slit inclination angle beta of the slotted circular turbulence column is 90 degrees, compared with a conventional laminate cooling system, the turbulence intensity of gas in the cooling channel can be increased, and the heat exchange capacity of the gas flow is improved.
Description
Technical Field
The utility model relates to a gas turbine cooling technology field especially relates to a plywood cooling structure of circular turbulent flow post is slotted in area.
Background
The pre-turbine temperature of turbocharged engines has reached 2000K at present and has increased year by year at an average rate of increase of 20 c per year. Far exceeds the temperature resistance of the existing metal material. In order to meet the temperature resistance requirements of turbine blades, cooling techniques are required to maximize cooling efficiency as much as possible.
According to the working principle of the gas turbine, most of high pressure obtained by compressing air by the air compressor is used for participating in combustion reaction, and the generated heat energy pushes turbine blades to do work; a small portion of the gas is required to cool the high temperature components of the gas turbine by bleed air, and the more this portion of the gas is consumed, the less efficient the compressor. In order to ensure the efficient operation of the engine and the safe and reliable operation of the turbine, the development of an efficient turbine cooling technology with higher cooling efficiency and less cold air consumption is required.
At present, a plurality of achievements have been made in the efficient turbine cooling technology, wherein the laminar cooling technology provided with the turbulence columns is one of the effective measures for cooling the turbine blades. The turbulator posts may be located anywhere in the internal cooling passageway of the turbine blade, and are currently typically located at the trailing edge of the blade. The cooling gas flowing through the cooling channel increases the turbulence intensity thereof through the turbulence of the turbulence columns, increases the heat exchange intensity with the wall surface of the laminate, and the turbulence columns can also serve as heat transfer elements, so that the cooling efficiency of the laminate cooling technology is increased.
The shape of the turbulence column is an important factor affecting the cooling efficiency of the laminate. At present, the square turbulence columns which are researched more have better heat exchange strength, but have larger flow resistance; the elliptical and water drop-shaped turbulence column has a low resistance coefficient, but the heat exchange strength is limited.
Disclosure of Invention
An object of the utility model is to solve the above-mentioned problem among the prior art, provide a circular baffling post's plywood cooling structure is slotted in area, improve the baffling post shape to further improve the cooling efficiency of its structure, with its heat transfer ability of maximize when reducing bleed volume in the hope.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a laminate cooling structure with a slotted circular turbulence column comprises an outer side plate, an inner side plate and a slotted circular turbulence column; the outer side plate is provided with an inclined gas film hole, and the outer side plate is a gas side; the inner side plate is provided with an impact hole and is a cold air side; the slotted circular spoiler column is arranged in a cooling channel formed between the outer side plate and the inner side plate; the cooling gas firstly impacts the outer side plate through the impact holes and enters the cooling channel to exchange heat with the turbulence columns in an enhanced manner, and then flows out along the air film holes of the outer side plate.
The slotted circular spoiler column is obtained by slotting on the basis of the reference circular spoiler column; the arrangement mode of the slotted circular turbulence columns is in parallel arrangement or in staggered arrangement.
The diameter d of the slotted circular turbulent flow column is 0.5-2.0 mm, and the height H is 0.5-2.0 mm.
The ratio of the seam width S to the diameter d of the slotted circular turbulent flow column is 0.1-0.5.
The gaps of the slotted circular turbulent flow column and the cold airflow direction V0The inclination angle beta of the gap between the two is 0-90 degrees.
The spanwise distance P of the slotted circular turbulent flow columns is 1.5 d-3 d.
The flow direction spacing W of the slotted circular turbulence columns is 1.5 d-3 d.
The film hole and the main flow direction V1The included angle alpha is 30-90 degrees.
Diameter D of the air film holeoutIs 0.5d to 1 d.
Diameter D of the impingement holeinIs 0.5 d-1.5 d.
Compared with the prior art, the utility model discloses technical scheme obtains beneficial effect is:
1. for a general laminate cooling structure, the turbulence column mainly adopted by the laminate cooling structure is in a circular column shape, the back of the turbulence column is provided with a dead zone where cooling gas can not reach or rarely reaches, and the heat exchange effect is poor. In the utility model, when the gap inclination angle beta is 0 degrees, the gas flows into the 'dead zone' on the back of the turbulence column through the gap structure, so that the uniformity of laminate cooling can be improved; when the inclination angle beta of the gap is 90 degrees, the blunt body flows around again after the gas passes through the gap to form a boundary layer, and the flow condition behind the cylinder can also be improved.
2. The turbulent column structure with the gap inclination angle beta of 0 degrees reduces the windward area of the turbulent column, and unloads at the highest pressure point, so that the pressure loss of cooling gas can be reduced, the heat exchange area between the turbulent column and the airflow is increased by the inner wall surface of the gap, and the loss of heat exchange capacity caused by the slotted structure can be reduced. The turbulent flow column structure with the gap inclination angle beta of 90 degrees increases the turbulent flow strength of air flow in the cooling channel, so that the turbulence degree of cooling air is increased, the average Nurseel number of the plate surface outside the channel is calculated, and the average Nurseel number of the design is higher than that of a circular turbulent flow column and an oval turbulent flow column, namely, the heat exchange strength can be increased compared with a layer plate cooling structure with a reference cylinder.
3. The utility model discloses a circular turbulence post that cracks can be used for multiple part, for example gas turbine engine's turbine blade, combustion chamber wall etc. and application scope is wide.
Drawings
Fig. 1 is a schematic side view of the present invention;
fig. 2 is a schematic perspective view of a slotted circular spoiler column, wherein (a) is a slotted circular spoiler column diagram with a slot inclination angle β equal to 90 °, and (b) is a slotted circular spoiler column diagram with a slot inclination angle β equal to 0 °;
FIG. 3 is a schematic plan view of a slotted circular turbulence column;
fig. 4 is a schematic diagram of an internal structure of the present invention, in which (a) is a structural diagram of laminate cooling with a slit inclination angle β equal to 90 °, and (b) is a structural diagram of laminate cooling with a slit inclination angle β equal to 0 °;
fig. 5 is a schematic top view of the present invention, wherein (a) is a plan view of a laminate cooling structure with a slit inclination angle β being 90 °, and (b) is a plan view of a laminate cooling structure with a slit inclination angle β being 0 °.
Reference numerals: 1-air film hole, 2-slotted circular turbulent flow column and 3-impact hole.
Detailed Description
In order to make the technical problem, technical solution and beneficial effects to be solved by the present invention clearer and more obvious, the following description is made in detail with reference to the accompanying drawings and embodiments.
As shown in fig. 1-3, the utility model is applied to a turbine blade, and comprises an outer side plate, an inner side plate and a slotted circular turbulent flow column 2; the inner side plate is an air inlet plate and is close to the cold air side, and the inner side plate is uniformly and equidistantly provided with a main air flow direction (a main flow direction V) perpendicular to the main air flow direction1) A plurality of impingement holes 3; the outer side plate is an air outlet plate, the outer side plate is close to the gas side, and inclined gas film holes 1 are formed in the outer side plate; the slotted circular turbulence columns 2 are arranged in the cooling channel formed between the outer side plate and the inner side plate in a row or in a fork row manner; the air film holes 1 are arranged between the two rows of slotted circular turbulence columns 2.
The slotted circular flow disturbing column 2 is composed of two semi-cylinders obtained by slotting the middle of a reference circular flow disturbing column.
The diameter d of the slotted circular turbulent flow column 2 is 0.5-2.0 mm, and the height H is 0.5-2.0 mm. The ratio of the seam width S to the diameter d of the slotted circular turbulent flow column 2 is 0.1-0.5.
As shown in fig. 3, in the cooling passage, the direction of the cold air flow V0And the main flow direction V1In accordance, the gap of the slotted circular turbulent flow column 2 and the cold air flow direction V0The inclination angle beta of the gap between the two plates is 0-90 degrees, and through simulation calculation, when the angle beta is 0 degree, the gap structure plays an unloading role, so that the pressure loss of the laminate cooling structure can be obviously reduced compared with a reference cylinder; when the beta is 90 degrees, the average heat exchange Knoop number of the airflow and the wall surface of the heat source is larger than that of a laminated plate structure with a reference cylinder in a certain inflow Reynolds number range, namely the heat exchange capability is enhanced.
As shown in fig. 5, the distance between two rows of slotted circular turbulence columns 2 is a span-wise pitch P, the span-wise pitch P is 1.5d to 3d, the distance between two rows of slotted circular turbulence columns 2 is a flow direction pitch W, and the flow direction pitch W is 1.5d to 3 d.
Diameter D of the gas film hole 1outIs 0.5d to 1 d. The diameter D of the impingement hole 3inIs 0.5 d-1.5 d.
As shown in fig. 1, the air film hole 1 is aligned with the main flow direction V1The included angle alpha is 30 degrees to 90 degrees, when the included angle alpha is smaller than 90 degrees, the cooling gas which flows out is more favorable for forming a gas film with the outer wall surface of the outer side plate, the normal momentum of the cold gas which flows out is reduced, the cold gas forms a better gas film on the outer wall surface, and the blade structure is protected.
The working principle of the utility model is as follows: cold source gas enters the inner cavity of the turbine blade through air compressor bleed air, cooling gas in the inner cavity impacts the outer side plate through impact holes 3 in the inner side plate, after the circular turbulent flow column 2 of the cooling channel cracks for turbulent flow, the turbulent flow strength of the gas is increased, the formed vortex structure can increase the utilization rate of the cooling gas, then the cooling gas flows into the grid channel of the blade through the gas film holes 1, and gas film cooling is formed by the cooling gas and the main air flow of the heat source of the outer side plate.
Example 1
The present embodiment is a laminate cooling structure with slotted circular spoiler columns 2 applied to turbine blades, fig. 4(a) and fig. 5(a) show an internal view and a plan view of a slotted circular spoiler column 2 with a diameter β of 90 ° in an inline condition, respectively, the slotted circular spoiler column 2 is obtained by slotting a reference cylinder with a diameter d of 0.8mm in a direction with a diameter β of 90 °, a slot width S is 0.12mm, a span-wise pitch P and a flow-wise pitch W are both 2.4mm, and the slotted circular spoiler columns 2 in front and rear rows are arranged in an inline manner. The diameter D of the inner side plate of the cold air side is opened along the vertical directioninThe air conditioner is characterized in that a plurality of impact holes 3 with the diameter of 0.8mm are formed, the inner edges of the holes are subjected to chamfering treatment, the span-wise distance and the flow direction distance of the impact holes 3 are 4.8mm, the impact holes and the flow direction distance are arranged in a staggered mode, air conditioner firstly impacts an outer side plate through the impact holes 3 and then enters a cooling channel to perform enhanced heat exchange with a slotted circular turbulence column 2, the air conditioner is subjected to flow guiding due to the fact that the pressure in the slot is smaller after being separated through a boundary layer of a front type semi-cylindrical structure, the separated air conditioner needs to flow around a next type semi-cylindrical structure again, and the utilization efficiency of the airHigh, simultaneously also improved the refrigerated homogeneity of outer panel, the gas after the vortex flows out along outer panel gas film hole 1, diameter DoutThe air film holes 1 with the thickness of 0.4mm are arranged at the position staggered with the impact holes 3, the span-wise distance and the flow-direction distance of the air film holes 1 are both 4.8mm, and the air film holes 1 and the main flow direction V of the gas1The included angle alpha is 30 degrees, and after cold air flows through the inclined air film hole 1, a better attached air film can be formed behind the air film hole 1 and on the outer side of the outer side plate, so that the blades are well protected.
Example 2
The embodiment is a laminate cooling structure with slotted circular turbulence columns 2 applied to turbine blades, fig. 4(b) and fig. 5(b) show an internal view and a top view of a slotted circular turbulence column 2 with a diameter β equal to 0 ° under a forking condition, respectively, the slotted circular turbulence column 2 is obtained by slotting a reference cylinder with a diameter d of 0.8mm in a direction with a diameter β equal to 0 °, the slot width S is 0.12mm, the span-wise distance P and the flow-wise distance W are both 2.4mm, and the slotted circular turbulence columns 2 in front and rear rows are arranged in a forking manner. The diameter D of the inner side plate of the cold air side is opened along the vertical directioninThe air compressor is characterized in that the air compressor is provided with a plurality of impact holes 3 of 0.8mm, the inner edges of the holes are subjected to chamfering treatment, the span-wise distance and the flow direction distance of the impact holes 3 are 4.8mm and are arranged in the same row with the slotted circular turbulence columns 2, air conditioning firstly impacts the outer side plate through the impact holes 3 and then enters the cooling channel to perform enhanced heat exchange with the turbulence columns, the air conditioning entering the cooling channel through the impact holes 3 quickly impacts the lower turbulence columns arranged in a staggered manner, stagnation points are formed right in front of the reference circular turbulence columns, the pressure is highest, after 0-degree slot opening, fluid at the stagnation points is unloaded, a horseshoe vortex structure with smaller flow behind the slotted impact columns is adopted, the cooling uniformity of the outer side plate is improved, the most important effect is that the on-way pressure loss is reduced, and therefore the working efficiency of the air compressor is improved. The gas after turbulent flow flows out along the gas film hole 1 of the outer side plate with the diameter DoutThe air film holes 1 with the thickness of 0.4mm are arranged at the same row position with the impact holes 3, the span-wise distance and the flow-direction distance of the air film holes 1 are both 4.8mm, and the air film holes 1 and the main flow direction V of the gas1The included angle alpha is 30 degrees, after cold air flows through the inclined air film hole 1, a better attached air film can be formed behind the air film hole 1 and outside the outer side plate, and the air film plays a good role in the bladesThe protective effect of (1).
Claims (10)
1. The utility model provides a plywood cooling structure of circular turbulent flow post is slotted in area which characterized in that: comprises an outer side plate, an inner side plate and a slotted circular turbulent flow column; the outer side plate is provided with an inclined gas film hole and is close to the gas side; the inner side plate is provided with an impact hole and is close to the cold air side; the slotted circular spoiler column is arranged in a cooling channel formed between the outer side plate and the inner side plate; the cooling gas firstly impacts the outer side plate through the impact holes and enters the cooling channel to exchange heat with the turbulence columns in an enhanced manner, and then flows out along the air film holes of the outer side plate.
2. A laminate cooling structure with slotted circular turbulator columns in accordance with claim 1, wherein: the slotted circular spoiler column is obtained by slotting on the basis of the reference circular spoiler column; the arrangement mode of the slotted circular turbulence columns is in parallel arrangement or in staggered arrangement.
3. A laminate cooling structure with slotted circular turbulator columns in accordance with claim 1, wherein: the diameter d of the slotted circular turbulent flow column is 0.5-2.0 mm, and the height H is 0.5-2.0 mm.
4. A laminate cooling structure with slotted circular turbulator columns in accordance with claim 3, wherein: the ratio of the seam width S to the diameter d of the slotted circular turbulent flow column is 0.1-0.5.
5. A laminate cooling structure with slotted circular turbulator columns in accordance with claim 1, wherein: the gaps of the slotted circular turbulent flow column and the cold airflow direction V0The inclination angle beta of the gap between the two is 0-90 degrees.
6. A laminate cooling structure with slotted circular turbulator columns in accordance with claim 3, wherein: the spanwise distance P of the slotted circular turbulent flow columns is 1.5 d-3 d.
7. A laminate cooling structure with slotted circular turbulator columns in accordance with claim 3, wherein: the flow direction spacing W of the slotted circular turbulence columns is 1.5 d-3 d.
8. A laminate cooling structure with slotted circular turbulator columns in accordance with claim 1, wherein: the film hole and the main flow direction V1The included angle alpha is 30-90 degrees.
9. A laminate cooling structure with slotted circular turbulator columns in accordance with claim 3, wherein: diameter D of the air film holeoutIs 0.5d to 1 d.
10. A laminate cooling structure with slotted circular turbulator columns in accordance with claim 3, wherein: diameter D of the impingement holeinIs 0.5 d-1.5 d.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020345598.9U CN211715181U (en) | 2020-03-18 | 2020-03-18 | Laminate cooling structure with slotted circular turbulence column |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020345598.9U CN211715181U (en) | 2020-03-18 | 2020-03-18 | Laminate cooling structure with slotted circular turbulence column |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211715181U true CN211715181U (en) | 2020-10-20 |
Family
ID=73396367
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020345598.9U Expired - Fee Related CN211715181U (en) | 2020-03-18 | 2020-03-18 | Laminate cooling structure with slotted circular turbulence column |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211715181U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113090411A (en) * | 2021-04-23 | 2021-07-09 | 西北工业大学 | Three-duct S-shaped bent spray pipe with turbulence rib-air film cooling structure |
| CN113358336A (en) * | 2021-04-25 | 2021-09-07 | 西北工业大学 | Laminate cooling structure test simulation piece, design method thereof and fatigue test device |
| CN113483354A (en) * | 2021-07-16 | 2021-10-08 | 西北工业大学 | Bent truss structure heat shield for afterburner and method for forming gas film |
| CN113669756A (en) * | 2021-08-31 | 2021-11-19 | 西北工业大学 | Double-layer double-effect heat insulation wall for afterburner cavity and double-effect cooling method |
| CN113929467A (en) * | 2021-10-14 | 2022-01-14 | 西安鑫垚陶瓷复合材料有限公司 | Preparation method of SiC/SiC ceramic composite blade body component with small turbulence column cooling gap |
| CN114353122A (en) * | 2022-01-23 | 2022-04-15 | 西北工业大学 | Combustion chamber flame cylinder wall laminate cooling structure with Y-shaped turbulence columns |
| CN114382553A (en) * | 2021-12-26 | 2022-04-22 | 西北工业大学 | High-blockage-ratio rib laminate cooling structure and cooling method for middle chord area of turbine blade |
| CN114412645A (en) * | 2021-12-26 | 2022-04-29 | 西北工业大学 | Cooling structure and cooling method of laminated plate with slit ribs for turbofan engine combustion chamber |
| CN115095390A (en) * | 2022-05-20 | 2022-09-23 | 南京航空航天大学 | Structure for improving laminate cooling performance by utilizing heat pipe |
-
2020
- 2020-03-18 CN CN202020345598.9U patent/CN211715181U/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113090411B (en) * | 2021-04-23 | 2023-02-10 | 西北工业大学 | Three-duct S-shaped bent spray pipe with turbulence rib-air film cooling structure |
| CN113090411A (en) * | 2021-04-23 | 2021-07-09 | 西北工业大学 | Three-duct S-shaped bent spray pipe with turbulence rib-air film cooling structure |
| CN113358336A (en) * | 2021-04-25 | 2021-09-07 | 西北工业大学 | Laminate cooling structure test simulation piece, design method thereof and fatigue test device |
| CN113358336B (en) * | 2021-04-25 | 2024-01-26 | 西北工业大学 | Laminate cooling structure test simulation piece, design method thereof and fatigue test device |
| CN113483354A (en) * | 2021-07-16 | 2021-10-08 | 西北工业大学 | Bent truss structure heat shield for afterburner and method for forming gas film |
| CN113669756A (en) * | 2021-08-31 | 2021-11-19 | 西北工业大学 | Double-layer double-effect heat insulation wall for afterburner cavity and double-effect cooling method |
| CN113669756B (en) * | 2021-08-31 | 2022-05-10 | 西北工业大学 | Double-layer double-effect heat insulation wall for afterburner cavity and double-effect cooling method |
| CN113929467A (en) * | 2021-10-14 | 2022-01-14 | 西安鑫垚陶瓷复合材料有限公司 | Preparation method of SiC/SiC ceramic composite blade body component with small turbulence column cooling gap |
| CN113929467B (en) * | 2021-10-14 | 2023-02-14 | 西安鑫垚陶瓷复合材料有限公司 | Preparation method of SiC/SiC ceramic composite blade body component with small turbulence column cooling gap |
| CN114382553A (en) * | 2021-12-26 | 2022-04-22 | 西北工业大学 | High-blockage-ratio rib laminate cooling structure and cooling method for middle chord area of turbine blade |
| CN114412645B (en) * | 2021-12-26 | 2023-01-31 | 西北工业大学 | Cooling structure and cooling method of laminated plate with slit ribs for turbofan engine combustion chamber |
| CN114412645A (en) * | 2021-12-26 | 2022-04-29 | 西北工业大学 | Cooling structure and cooling method of laminated plate with slit ribs for turbofan engine combustion chamber |
| CN114353122A (en) * | 2022-01-23 | 2022-04-15 | 西北工业大学 | Combustion chamber flame cylinder wall laminate cooling structure with Y-shaped turbulence columns |
| CN115095390A (en) * | 2022-05-20 | 2022-09-23 | 南京航空航天大学 | Structure for improving laminate cooling performance by utilizing heat pipe |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN211715181U (en) | Laminate cooling structure with slotted circular turbulence column | |
| CN103967621B (en) | There is the refrigerating unit of small diagonal rib-depression composite structure | |
| CN110030036B (en) | Impact split-joint air film cooling structure of turbine blade tail edge | |
| CN107035421A (en) | A kind of turbine blade tail flow-disturbing with array pin rib partly splits seam cooling structure | |
| CN111764967B (en) | Turbine blade trailing edge cooling structure | |
| CN104791020A (en) | Gas turbine blade with longitudinal crossed rib cooling structure | |
| CN112459852B (en) | Be applied to two water conservancy diversion rib water conservancy diversion structures of turbine blade trailing edge half-splitting seam | |
| CN111305906A (en) | Area is disconnected straight rib and is half split joint cooling structure between suitable for high temperature turbine blade | |
| CN107060893A (en) | A kind of turbine blade tail flow-disturbing with V-type rib partly splits seam cooling structure | |
| CN113047912A (en) | Laminate cooling structure with quincunx turbulence columns | |
| CN112746870B (en) | Interrupted wave rib cooling structure | |
| CN113374536B (en) | Gas turbine guide vane | |
| CN107013255A (en) | A kind of turbine blade tail flow-disturbing with continuous straight rib partly splits seam cooling structure | |
| CN103075202A (en) | Impingement cooling structure with grid turbulence effect in turbine blade | |
| CN115898693A (en) | Corrugated turbulent flow plane cooling device and application | |
| CN114109515B (en) | Turbine blade suction side cooling structure | |
| Cheng et al. | Effect of film-hole configuration on film-cooling effectiveness of squealer tips | |
| CN204609950U (en) | Gas turbine blade with longitudinal crossed rib cooling structure | |
| CN112343667B (en) | Continuous V-shaped rib flow guide structure applied to turbine blade trailing edge half-splitting seam | |
| CN112523810B (en) | Triangular column type flow guide structure applied to turbine blade trailing edge half-splitting seam | |
| CN113123832B (en) | Double-wall herringbone turbulence column structure for impact turbulence air film composite cooling | |
| CN214170628U (en) | Spherical concave structure for cooling turbine blade | |
| CN114109514A (en) | Turbine blade pressure surface cooling structure | |
| CN112343666A (en) | Be applied to half corrugated rib water conservancy diversion structure of splitting seam of turbine blade trailing edge | |
| CN111335963B (en) | Wing section spoiler column structure and turbine blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201020 Termination date: 20210318 |