CN113374545A - Impingement cooling structure based on array annular raised target plate - Google Patents
Impingement cooling structure based on array annular raised target plate Download PDFInfo
- Publication number
- CN113374545A CN113374545A CN202110715346.XA CN202110715346A CN113374545A CN 113374545 A CN113374545 A CN 113374545A CN 202110715346 A CN202110715346 A CN 202110715346A CN 113374545 A CN113374545 A CN 113374545A
- Authority
- CN
- China
- Prior art keywords
- impact
- target plate
- annular
- array
- holes
- 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.)
- Pending
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 45
- 239000000112 cooling gas Substances 0.000 claims abstract description 4
- 238000000034 method Methods 0.000 claims description 3
- 239000012530 fluid Substances 0.000 abstract description 10
- 230000000694 effects Effects 0.000 abstract description 9
- 238000005728 strengthening Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 abstract 2
- 230000003014 reinforcing effect Effects 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000003313 weakening effect Effects 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
Abstract
The invention relates to an impingement cooling structure based on an array annular raised target plate, belonging to the field of engine turbines; the gas-film impact device comprises a gas inlet cavity, an impact plate, an impact target plate, and an array annular bulge and a plurality of gas film holes which are arranged on the impact target plate, wherein each annular bulge is positioned between adjacent impact holes in the flow direction, and the span-wise distance and the flow-direction distance of the array annular bulge are consistent with the span-wise distance and the flow-direction distance of the impact holes; the plurality of air film holes are positioned downstream of the array annular bulges on the impact target plate along the flow direction; the cooling gas vertically shoots to the impact target plate through the impact holes, passes through the annular bulge after being bent for 90 degrees on the impact target plate, flows to the downstream air film holes, and flows out of the air film holes to be cooled externally. The array annular bulge increases the heat exchange area so as to achieve the purposes of increasing the heat exchange quantity and strengthening the heat exchange effect; and the annular bulge can perform secondary disturbance on the fluid in the flow direction, so that the disturbance is enhanced, and the heat exchange is enhanced.
Description
Technical Field
The invention belongs to the field of engine turbines, and particularly relates to an impingement cooling structure based on an array annular raised target plate.
Background
With the continuous development of aircraft engine technology, the front inlet temperature of the turbine reaches about 2000K, and far exceeds the melting point of the material for manufacturing high-temperature components. The turbine blade is cooled necessarily, the whole temperature level and the local temperature difference of the turbine blade are reduced, the turbine blade is guaranteed not to be seriously deformed or ablated in a required working range, and the turbine blade cooling device has very important significance for long service life and safe operation. Modern aircraft engine turbine blades achieve the goal of cooling the blade through a reasonable coordination of internal and external cooling. Among them, impingement cooling is a form of convective heat transfer with the strongest heat transfer effect among internal cooling.
In the impact heat transfer, the impact jet flow is shot to the target surface through the impact holes to exchange heat with the impact target surface, so that the heat inside the blade is taken away, and the whole blade is cooled. In a practical engine, when the impinging fluid impacts the target surface, the fluid surrounding the target surface is influenced, usually flowing, by the upstream impinging jet, creating a cross-flow effect. Due to the presence of cross flow, the impingement jet is forced to deflect in the direction of cross flow, weakening the impingement cooling intensity. In recent years, various concave pits or convex structures are arranged on an impact target surface and combined with impact cooling, so that the influence of upstream cross flow on impact jet flow can be weakened, the turbulence degree and the heat exchange area near the target surface can be increased, and the heat exchange is enhanced.
For the pit structure, patent CN110195615A has given a cross-section for semicircular slot, for the enhancement of plane target plate heat transfer, nevertheless to the disturbance of flow for the wall face ization, the influence only exists in the one deck fluid near the wall face, the effect of intensive heat transfer receives certain restriction, and the dust is gathered easily to the pit structure simultaneously, and is difficult for wasing, and this can influence impact heat transfer intensity to a certain extent, can produce certain influence to aeroengine performance. Compared with a pit structure, the influence of the convex structure does not tend to be wall-surface, and the inhibition effect on the upstream transverse flow is more obvious.
In the study of the bump structure, the study is usually conducted only on the structure with the conventional shape, or only the geometric parameters and arrangement of the bump structure with the conventional shape, and the analysis of the bump structure with the special shape, such as Wuweilong, is lacked[1]Cylinder of the same people researchThe shape turbulent flow structure can not provide sufficient basis for the selection of the impact cooling target surface structure. Meanwhile, the raised structures arranged on the target plate in the prior art are various ribs, so that disturbance can be enhanced generally, the heat exchange area is increased, and the flow state of jet flow and transverse flow is changed. However, after the raised ribs are arranged, although the heat exchange area is increased, and therefore the heat exchange coefficient is increased, a larger pressure loss is generated at the same time, so that the impact heat exchange flow rate is reduced under the same pressure difference, and the ribs can also block the cooling jet from impacting the area near the bottoms of the fins on the target plate.
Reference documents:
[1] wuweilong, Xuhua Showa, Wangjianhua, numerical analysis of the flow of cold air in the trailing edge channel of turbine blades with turbulence columns [ J ] propulsion technique 2021,42(01): 163-.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides an impact cooling structure based on an array annular protrusion target plate, wherein the array annular protrusion is arranged on the target plate, and cold air is ejected from an impact hole, vertically ejected to the impact target plate, passes through the annular protrusion and flows to a downstream air film hole; the array annular bulge additionally arranged on the target plate increases the heat exchange area so as to achieve the purposes of increasing the heat exchange quantity and strengthening the heat exchange effect; and the annular bulge can perform secondary disturbance on the fluid in the flow direction, so that the disturbance is enhanced, and the heat exchange is enhanced. Therefore, the invention aims to solve the problems that the pit structure disturbs the wall surface, the bulge structure is single, larger pressure loss is generated and the like in the prior art.
The technical scheme of the invention is as follows: an impact cooling structure based on an array annular raised target plate comprises an air inlet cavity, an impact plate and an impact target plate, wherein cooling air enters the air inlet cavity and vertically shoots to the surface of the impact target plate through impact holes in the impact plate; the method is characterized in that: the array annular bulge is arranged on the impact target plate, the air film holes are formed in the array annular bulge, the annular bulge is arranged between the impact holes adjacent in the flow direction, and the spanwise spacing and the flow direction spacing of the array annular bulge are consistent with those of the impact holes; the plurality of air film holes are positioned downstream of the array annular bulges on the impact target plate along the flow direction; the cooling gas vertically shoots to the impact target plate through the impact holes, passes through the annular bulge after being bent for 90 degrees on the impact target plate, flows to the downstream air film holes, and flows out of the air film holes for external cooling;
the distance between the impact plate and the impact target plate is an impact distance H, and the diameter of the impact hole is d.
The further technical scheme of the invention is as follows: the impact distance H is 1.8-2.2 d; the distance between adjacent impact holes along the flow direction is 9-11 d, and the distance between adjacent impact holes along the span direction is 7-9 d.
The further technical scheme of the invention is as follows: the outlet center of the impingement hole in the first row is 10 film hole diameters from the nearest exhaust film hole inlet center in the flow direction.
The further technical scheme of the invention is as follows: the annular bulge is an annular structure with a semicircular radial section, the bottom plane of the annular bulge is fixed on the impact target plate in parallel, and the semicircular ring is positioned above the impact target plate.
The further technical scheme of the invention is as follows: the diameter of the semicircle of the radial section of the annular bulge is 0.3-0.4 d, and the distance between the center of the semicircle and the center of the annular bulge is 0.6-0.7 d.
The further technical scheme of the invention is as follows: the annular protrusions are located at the midpoint between the impact holes adjacent in the flow direction, namely the centers of every two adjacent impact jets in the flow direction.
The further technical scheme of the invention is as follows: the incident angle of the air film hole is 15-45 degrees.
Advantageous effects
The invention has the beneficial effects that: the invention provides an impingement cooling structure based on an array annular convex target plate, namely an annular convex structure is arranged on a turbine blade impingement cooling target plate. The concrete advantages are as follows:
1. compared with a cylindrical turbulence structure, the annular protrusion structure is low in height and small in resistance under the same size, the extending distance is larger than that of the cylindrical structure, the flowing direction of fluid is changed, transverse mixing of the fluid is promoted, the overall heat exchange of the target surface is increased, and the heat exchange is more uniform.
2. Compare in cylinder vortex structure, the fluid gets into the centre of a circle behind the annular arch, and protruding structure can flow out afterwards, and the impingement cooling structure based on protruding target plate of array annular can carry out the secondary disturbance to the fluid in the flow direction to the disturbance reinforcing, the heat transfer reinforcing.
3. Compare in pit structure, the annular protruding structure can carry out the disturbance to the deeper depth of boundary layer, and the effect reinforcing of intensive heat transfer.
4. The shapes of the convex structures are enriched, and a basis is provided for selection of the structure of the impact cooling target surface.
5. The bulge structure is arranged in the non-impact area, so that the thicker boundary layer can be disturbed, and the overall heat transfer effect of the target surface is enhanced.
Based on the impact cooling structure based on the array annular raised target plate, numerical simulation is carried out under the working condition that the inlet speed of the cold air cavity is 0.5 m/s. The annular convex structures are positioned on the impact target plate, the span-wise distance is 24mm, and the flow-direction distance is 30 mm. The air film holes are positioned on one side of the impact target plate, which is not just opposite to the impact holes, the diameter of the air film holes is 2.8mm, the intervals of the flow direction and the expansion direction are both 12mm, and the included angle between the axis of the air film holes and the impact target surface is 30 degrees. The diameter of the impact holes is 3mm, the flow direction and the span direction spacing are consistent with the annular bulge structure, the distance between the first row of impact holes and the center of the nearest air film hole is 28mm, and the annular bulge structure is not arranged between the first row of impact holes and the center of the nearest air film hole. The protruding structure of annular is located between two impact jet centers, and protruding structure is formed around the bellied center rotation of annular by a semicircle, and semicircle diameter is 1mm, and the semicircle centre is 2mm apart from the bellied center of annular, and the rotatory inner ring diameter that obtains of the protruding structure of annular on strikeing the target surface is 3mm, and the outer loop diameter is 5 mm. The numerical simulation result is as shown in fig. 8, and the impingement cooling structure based on the array annular raised target plate can increase the heat exchange strength of the target surface to a certain extent compared with the cylindrical raised target plate with the same volume, so that the heat exchange of the target surface is more uniform.
The setting of the impact distance can be more fit with the actual impact cooling size, the arrangement of the array annular bulge structure ensures that the jet flow can be converged with downstream impact jet flow after being disturbed by the annular bulge structure on the target surface, and the size of the bulge structure can ensure that the fluid is disturbed, the heat exchange area is increased, and meanwhile, unnecessary flow loss can not be excessively increased.
Drawings
FIG. 1 is a front view of an impingement cooling structural unit based on an array of annular raised target plates of the present invention.
FIG. 2 is a top view of an impingement cooling structure unit based on an array of annular raised target plates of the present invention.
FIG. 3 is a bottom view of an impingement cooling structure unit based on an array annular raised target plate of the present invention.
FIG. 4 is an isometric view of an impingement cooling structure unit based on an array of annular raised target plates of the present invention.
FIG. 5 is an isometric view of an impingement cooling structural unit impingement target plate based on an array annular raised target plate of the present invention.
FIG. 6 is a cross-sectional view of an impingement cooling structure unit based on an array of annular raised target plates of the present invention.
FIG. 7 is a perspective view of an impingement cooling structural unit impingement target plate based on an array annular raised target plate of the present invention.
FIG. 8 is a comparison graph of heat transfer coefficients of an impingement cooling structure unit impingement target plate and a cylindrical target plate based on an array annular raised target plate under the conditions of the examples.
Description of reference numerals: 1. the impact target plate 2, the annular bulge 3, the cold air cavity 4, the air film hole 5, the impact hole 6 and the periodic surface of the heat exchange unit.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Referring to fig. 1-6, the impingement cooling structure based on the array annular protrusion target plate comprises an air inlet cavity 3, an impingement plate, an impingement target plate 1, an array annular protrusion 2 and a plurality of air film holes 4, wherein the array annular protrusion 2 and the air film holes 4 are arranged on the impingement target plate, and each annular protrusion 2 is located at the midpoint between adjacent impingement holes 5 in the flow direction, namely the centers of every two adjacent impingement jets in the flow direction. The span-wise distance and the flow direction distance of the array annular bulge 2 are consistent with those of the impact holes 5; a plurality of air film holes 4 are positioned at the downstream of the array annular bulge 2 on the impact target plate 1 along the flow direction; the cooling gas vertically shoots to the impact target plate 1 through the impact holes 5, passes through the annular bulge 2 after being bent for 90 degrees on the impact target plate 1, flows to the downstream air film holes 4, and flows out of the air film holes for external cooling.
The distance between the impact plate and the impact target plate is an impact distance H, and the diameter of the impact hole 5 is d. The impact distance H is 1.8-2.2 d; the distance between adjacent impact holes along the flow direction is 9-11 d, and the distance between adjacent impact holes along the span direction is 7-9 d. Wherein the outlet center of the impingement hole in the first row is 10 times the diameter of the film hole in the flow direction from the inlet center of the nearest exhaust film hole.
The annular bulge 2 is an annular structure with a semicircular radial section, the bottom plane of the annular bulge is fixed on the impact target plate in parallel, and the semicircular ring is positioned above the impact target plate. The diameter of the semicircle of the radial section of the annular bulge 2 is 0.3-0.4 d, and the distance between the center of the semicircle and the center of the annular bulge is 0.6-0.7 d.
The incident angle of the air film hole 4 is 15-45 degrees.
Example (b):
the utility model provides an impingement cooling structure based on protruding target plate of array annular, includes cold air chamber, jump bit, strikes target plate, annular arch, air film hole.
Referring to fig. 1, the annular raised structures 2 are located on the impact target plate at spanwise and streamwise spacings of 24mm and 30 mm. Referring to fig. 2, the air film holes are located on the side of the impact target plate not directly opposite to the impact holes, the diameter of the air film holes is 2.8mm, the flow direction and the span direction spacing of the air film holes are 12mm, and the included angle between the axis of the air film holes and the impact target surface is 30 degrees. Referring to fig. 3, the impingement holes are 3mm in diameter, the flow and span spacing is consistent with the annular raised structure, and the impingement holes in the first row are 28mm from the center of the nearest film hole, and there is no annular raised structure between them. Protruding structure is located between two impact jet centers for the efflux must pass through the disturbance back of annular protruding structure on the target surface, just can strike the efflux with low reaches and converge, and first row of impact hole can directly flow out from the air film hole through protruding structure of target surface owing to need not pass through other impact efflux.
Referring to fig. 5-7, the annular protrusion structure is formed by rotating a semicircle around the center of the annular protrusion, the diameter of the semicircle is 1mm, the distance between the center of the semicircle and the center of the annular protrusion is 2mm, the diameter of the inner ring of the annular protrusion structure on the impact target surface obtained by rotation is 3mm, and the diameter of the outer ring is 5 mm.
The numerical simulation result is as shown in fig. 8, and the impingement cooling structure based on the array annular raised target plate can increase the heat exchange strength of the target surface to a certain extent compared with the cylindrical raised target plate with the same volume, so that the heat exchange of the target surface is more uniform.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (7)
1. An impact cooling structure based on an array annular raised target plate comprises an air inlet cavity, an impact plate and an impact target plate, wherein cooling air enters the air inlet cavity and vertically shoots to the surface of the impact target plate through impact holes in the impact plate; the method is characterized in that: the array annular bulge is arranged on the impact target plate, the air film holes are formed in the array annular bulge, the annular bulge is arranged between the impact holes adjacent in the flow direction, and the spanwise spacing and the flow direction spacing of the array annular bulge are consistent with those of the impact holes; the plurality of air film holes are positioned downstream of the array annular bulges on the impact target plate along the flow direction; the cooling gas vertically shoots to the impact target plate through the impact holes, passes through the annular bulge after being bent for 90 degrees on the impact target plate, flows to the downstream air film holes, and flows out of the air film holes for external cooling;
the distance between the impact plate and the impact target plate is an impact distance H, and the diameter of the impact hole is d.
2. The impingement cooling structure based on an array of annular raised target plates of claim 1, wherein: the impact distance H is 1.8-2.2 d; the distance between adjacent impact holes along the flow direction is 9-11 d, and the distance between adjacent impact holes along the span direction is 7-9 d.
3. The impingement cooling structure based on an array of annular raised target plates of claim 1, wherein: the outlet center of the impingement hole in the first row is 10 film hole diameters from the nearest exhaust film hole inlet center in the flow direction.
4. The impingement cooling structure based on an array of annular raised target plates of claim 1, wherein: the annular bulge is an annular structure with a semicircular radial section, the bottom plane of the annular bulge is fixed on the impact target plate in parallel, and the semicircular ring is positioned above the impact target plate.
5. The impingement cooling structure based on an array of annular raised target plates of claim 4, wherein: the diameter of the semicircle of the radial section of the annular bulge is 0.3-0.4 d, and the distance between the center of the semicircle and the center of the annular bulge is 0.6-0.7 d.
6. The impingement cooling structure based on an array of annular raised target plates of claim 1, wherein: the annular protrusions are located at the midpoint between the impact holes adjacent in the flow direction, namely the centers of every two adjacent impact jets in the flow direction.
7. The impingement cooling structure based on an array of annular raised target plates of claim 1, wherein: the incident angle of the air film hole is 15-45 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110715346.XA CN113374545A (en) | 2021-06-27 | 2021-06-27 | Impingement cooling structure based on array annular raised target plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110715346.XA CN113374545A (en) | 2021-06-27 | 2021-06-27 | Impingement cooling structure based on array annular raised target plate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113374545A true CN113374545A (en) | 2021-09-10 |
Family
ID=77579400
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110715346.XA Pending CN113374545A (en) | 2021-06-27 | 2021-06-27 | Impingement cooling structure based on array annular raised target plate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113374545A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TW201116982A (en) * | 2009-11-13 | 2011-05-16 | Sunonwealth Electr Mach Ind Co | Cooling module |
| CN102374537A (en) * | 2010-08-12 | 2012-03-14 | 通用电气公司 | Combustor liner cooling system |
| EP2453109A1 (en) * | 2010-11-15 | 2012-05-16 | Alstom Technology Ltd | Gas turbine arrangement and method for operating a gas turbine arrangement |
| CN202417611U (en) * | 2011-12-28 | 2012-09-05 | 中航商用航空发动机有限责任公司 | Turbine blade |
| US20140290257A1 (en) * | 2011-12-15 | 2014-10-02 | Ihi Corporation | Impingement cooling mechanism, turbine blade and cumbustor |
| CN204555780U (en) * | 2015-01-14 | 2015-08-12 | 海信科龙电器股份有限公司 | A kind of heat exchange fin and heat exchanger |
| CN109883238A (en) * | 2019-03-08 | 2019-06-14 | 西安交通大学 | A kind of plate fin type heat exchanger core and its fin structure |
| CN110080828A (en) * | 2019-04-15 | 2019-08-02 | 西北工业大学 | A kind of grid seam gaseous film control structure exported with spool type turbulence columns and double roundings |
| CN112879103A (en) * | 2021-03-10 | 2021-06-01 | 西北工业大学 | Array impact air film structure based on ellipsoidal protrusions |
| CN112935127A (en) * | 2021-01-27 | 2021-06-11 | 浙江银轮机械股份有限公司 | Heat exchange tube manufacturing method and heat exchange tube |
-
2021
- 2021-06-27 CN CN202110715346.XA patent/CN113374545A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TW201116982A (en) * | 2009-11-13 | 2011-05-16 | Sunonwealth Electr Mach Ind Co | Cooling module |
| CN102374537A (en) * | 2010-08-12 | 2012-03-14 | 通用电气公司 | Combustor liner cooling system |
| EP2453109A1 (en) * | 2010-11-15 | 2012-05-16 | Alstom Technology Ltd | Gas turbine arrangement and method for operating a gas turbine arrangement |
| US20140290257A1 (en) * | 2011-12-15 | 2014-10-02 | Ihi Corporation | Impingement cooling mechanism, turbine blade and cumbustor |
| CN202417611U (en) * | 2011-12-28 | 2012-09-05 | 中航商用航空发动机有限责任公司 | Turbine blade |
| CN204555780U (en) * | 2015-01-14 | 2015-08-12 | 海信科龙电器股份有限公司 | A kind of heat exchange fin and heat exchanger |
| CN109883238A (en) * | 2019-03-08 | 2019-06-14 | 西安交通大学 | A kind of plate fin type heat exchanger core and its fin structure |
| CN110080828A (en) * | 2019-04-15 | 2019-08-02 | 西北工业大学 | A kind of grid seam gaseous film control structure exported with spool type turbulence columns and double roundings |
| CN112935127A (en) * | 2021-01-27 | 2021-06-11 | 浙江银轮机械股份有限公司 | Heat exchange tube manufacturing method and heat exchange tube |
| CN112879103A (en) * | 2021-03-10 | 2021-06-01 | 西北工业大学 | Array impact air film structure based on ellipsoidal protrusions |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6407276B2 (en) | Gas turbine engine component including trailing edge cooling using impingement angled to a surface reinforced by a cast chevron array | |
| CN108223022B (en) | Turbulent flow structure in array jet cooling | |
| CN202202899U (en) | Turbine cooling blade and turbine thereof | |
| CN211715181U (en) | Laminate cooling structure with slotted circular turbulence column | |
| CN111764967B (en) | Turbine blade trailing edge cooling structure | |
| CN102128055A (en) | Gas turbine cooling blade with crown | |
| CN111927562A (en) | Turbine rotor blade and aircraft engine | |
| CN110030036B (en) | Impact split-joint air film cooling structure of turbine blade tail edge | |
| CN110410158B (en) | Turbine rotor blade of gas turbine | |
| CN113090335A (en) | Impact air-entraining film double-wall cooling structure for turbine rotor blade | |
| CN113374536B (en) | Gas turbine guide vane | |
| CN112879103A (en) | Array impact air film structure based on ellipsoidal protrusions | |
| CN110145371A (en) | It is a kind of with conical boss and to open up to the target plate structure being interrupted straight rib and combining | |
| CN114109515B (en) | Turbine blade suction side cooling structure | |
| CN113123832B (en) | Double-wall herringbone turbulence column structure for impact turbulence air film composite cooling | |
| CN100489285C (en) | Ancient coin type flow-disturbing column veneer structure | |
| CN102588000A (en) | Internal cooling structure with grooves and ribs on front edge of turbine blade and method of internal cooling structure | |
| CN113374545A (en) | Impingement cooling structure based on array annular raised target plate | |
| CN114412645B (en) | Cooling structure and cooling method of laminated plate with slit ribs for turbofan engine combustion chamber | |
| CN113374546A (en) | Array impact structure based on circular truncated cone and cylindrical bulge | |
| CN214887244U (en) | Array impact air film structure based on ellipsoidal protrusions | |
| CN114382553A (en) | High-blockage-ratio rib laminate cooling structure and cooling method for middle chord area of turbine blade | |
| CN109083689B (en) | Recess, cooling structure, cooling assembly and method of forming recess | |
| CN218117856U (en) | Blade of gas turbine | |
| CN216642214U (en) | High-blockage-ratio finned laminate cooling structure for middle chord area of turbine blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210910 |
|
| RJ01 | Rejection of invention patent application after publication |