CN209040894U - A kind of aero engine turbine blades with refrigerating function - Google Patents
A kind of aero engine turbine blades with refrigerating function Download PDFInfo
- Publication number
- CN209040894U CN209040894U CN201821983882.8U CN201821983882U CN209040894U CN 209040894 U CN209040894 U CN 209040894U CN 201821983882 U CN201821983882 U CN 201821983882U CN 209040894 U CN209040894 U CN 209040894U
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- main body
- cold air
- blade main
- turbo blade
- spoiler
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Abstract
The utility model relates to contain aero-engine technology field, and disclose a kind of aero engine turbine blades with refrigerating function, including wheel disk of turbine, turbo blade main body and handle assembly, the turbo blade main body includes blade back, leaf basin, trailing edge, cold air inlet, cold air outlet, air film hole, cooling chamber, spoiler, cooling duct and flow-disturbing rib, the air film hole is provided with the outer surface of blade back, the top of the flow-disturbing rib is fixedly welded on the inner cavity top of turbo blade main body, one end of the spoiler is fixedly welded on the outside of flow-disturbing rib, the utility model passes through the air film hole in blade back and leaf basin, cool down cold air in the form of impinging cooling to the surface of blade back and leaf basin, and a part is flowed out by air film hole, one layer of cold air thin layer can be formed on the surface of blade, blade is effectively protected, simultaneously, it is internal The inner cavity of blade is equipped with spoiler and flow-disturbing rib, enhances the efficiency of internal heat, improves the cooling effect of entire blade.
Description
Technical field
The utility model relates to aero-engine technology field, specially a kind of aero-engine whirlpool with refrigerating function
Impeller blade.
Background technique
With the development of aeronautical technology, how to improve the efficiency of engine is always the project that we need to solve, for
For turbogenerator, the fuel gas temperature for improving turbine inlet can improve the performance of engine, however, the combustion gas of turbine inlet
Temperature is but limited by the temperature capacity of turbine material, so we must reduce turbo blade using the effectively type of cooling
Wall surface temperature, the common type of cooling includes gaseous film control, impinging cooling, turbulence columns enhanced heat exchange etc., but effect achieved
Fruit is different, is not able to satisfy increasingly advanced aeronautical technology, it would therefore be desirable to a kind of aeroplane engine with refrigerating function
Machine turbo blade has efficiently cooling effect, can keep up with the paces of people's aeronautical technology progress.
Utility model content
The purpose of this utility model is to provide a kind of aero engine turbine blades with refrigerating function, reach more
Kind type of cooling cooperation, and the purpose of cooling high-efficiency.
To achieve the above object, the utility model provides the following technical solutions: a kind of aeroplane engine with refrigerating function
Machine turbo blade, including wheel disk of turbine, turbo blade main body and handle assembly, the turbo blade main body are uniformly mounted on turbine
The outside of wheel disc, the handle assembly are welded on the bottom of turbo blade main body.
The turbo blade main body includes blade back, leaf basin, trailing edge, cold air inlet, cold air outlet, air film hole, cooling chamber, disturbs
The outside of turbo blade main body is arranged in flowing plate, cooling duct and flow-disturbing rib, the blade back, and the leaf basin is arranged in turbo blade
The top of turbo blade main body is arranged in the inside of main body, the trailing edge, and the cold air inlet is provided with turbo blade main body
Bottom, the cold air outlet are provided with the top of turbo blade main body, and the air film hole is provided with the outer surface of blade back, described cold
But the inner cavity of turbo blade main body is arranged in chamber, and the top of the flow-disturbing rib is fixedly welded on the inner cavity top of turbo blade main body
Portion, the cooling duct are mounted on the inside of cooling chamber, and one end of the spoiler is fixedly welded on the outside of flow-disturbing rib.
The handle assembly includes hub lumen, flank, dovetail, link block, airflow channel and bottom plate, and the bottom plate is fixed
It is welded on the bottom of turbo blade main body, the flank is fixedly connected on the two sides of bottom plate, and the hub lumen is provided with bottom plate
Bottom, the link block are fixedly welded on the inside of hub lumen, and the airflow channel is provided with the outside of link block, and one end connects
Cold air inlet is passed to, the dovetail is fixedly welded on the bottom of link block.
Preferably, the blade back and leaf basin include substrate and laminate, and the inside of the laminate is uniformly provided with channel.
Preferably, the surface of the leaf basin also is provided with air film hole, and the two sides of the air film hole are additionally provided with groove.
Preferably, it is also fixedly connected with spoiler on the side wall of the turbo blade body lumen, the spoiler and disturbs
Flow the spoiler interval setting on rib.
Preferably, there are four the cold air inlet and cold air outlet are all provided with, and cold air inlet and cold air outlet be not same
In perpendicular.
Preferably, the tip of the trailing edge also is provided with cold air path, and the spoiler is circular slab.
The utility model provides a kind of aero engine turbine blades with refrigerating function.Have following beneficial to effect
Fruit:
(1), the utility model is by the air film hole in blade back and leaf basin, make cold air in the form of impinging cooling to blade back and
The surface of leaf basin is cooled down, and a part is flowed out by air film hole, can form one layer of cold air thin layer on the surface of blade, right
The outer surface of blade effectively protects, meanwhile, the inner cavity of inner vanes is equipped with spoiler and flow-disturbing rib, enhances internal heat
Efficiency, improve the cooling effect of entire blade.
(2), the utility model is flowed through and is absorbed in the through-hole of laminate heat by laminate, cold air, can not only be reduced
The consumption of air, while heat exchange area is big, and good cooling results, in addition, can be improved whole by the way that spoiler is set as round
The exchange capability of heat of a spoiler further strengthens the cooling performance of entire blade interior, and whole device is compact-sized, rationally effectively
Ground is compounded with a variety of cooling provisions, keeps the cooling effect of entire blade more preferable.
Detailed description of the invention
FIG. 1 is a schematic structural view of the utility model；
Fig. 2 is the utility model installation effect diagram；
Fig. 3 is the utility model turbo blade body interior structural schematic diagram；
Fig. 4 is the layered structure schematic diagram of the utility model blade back and leaf basin.
In figure: 1 wheel disk of turbine, 2 turbo blade main bodys, 3 handle assemblies, 301 hub lumens, 302 flanks, 303 dovetails,
304 link blocks, 305 airflow channels, 306 bottom plates, 4 blade backs, 5 leaf basins, 6 trailing edges, 7 cold air inlets, 8 cold air outlets, 9 air film holes,
10 cooling chambers, 11 spoilers, 12 cooling ducts, 13 flow-disturbing ribs, 14 substrates, 15 laminates.
Specific embodiment
As shown in Figs 1-4, the utility model provides a kind of technical solution: a kind of aero-engine whirlpool with refrigerating function
Impeller blade, including wheel disk of turbine 1, turbo blade main body 2 and handle assembly 3, turbo blade main body 2 are uniformly mounted on wheel disk of turbine
1 outside, handle assembly 3 are welded on the bottom of turbo blade main body 2.
Turbo blade main body 2 includes blade back 4, leaf basin 5, trailing edge 6, cold air inlet 7, cold air outlet 8, air film hole 9, cooling chamber
10, the outside of turbo blade main body 2 is arranged in spoiler 11, cooling duct 12 and flow-disturbing rib 13, blade back 4, and leaf basin 5 is arranged in whirlpool
The top of turbo blade main body 2 is arranged in the inside of impeller blade main body 2, trailing edge 6, and cold air inlet 7 is provided with turbo blade main body 2
Bottom, cold air outlet 8 is provided with the top of turbo blade main body 2, and air film hole 9 is provided with the outer surface of blade back 4, cooling chamber 10
The inner cavity of turbo blade main body 2 is set, and the top of flow-disturbing rib 13 is fixedly welded on the inner cavity top of turbo blade main body 2, cold
But channel 12 is mounted on the inside of cooling chamber 10, and one end of spoiler 11 is fixedly welded on the outside of flow-disturbing rib 13.
Handle assembly 3 includes hub lumen 301, flank 302, dovetail 303, link block 304, airflow channel 305 and bottom plate
306, bottom plate 306 is fixedly welded on the bottom of turbo blade main body 2, and flank 302 is fixedly connected on the two sides of bottom plate 306, shank
Chamber 301 is provided with the bottom of bottom plate 306, and link block 304 is fixedly welded on the inside of hub lumen 301, and airflow channel 305 is provided with
The outside of link block 304, and one end is connected to cold air inlet 7, dovetail 303 is fixedly welded on the bottom of link block 304.
Blade back 4 and leaf basin 5 include substrate 14 and laminate 15, and the inside of laminate 15 is uniformly provided with channel, the surface of leaf basin 5
It also is provided with air film hole 9, the two sides of air film hole 9 are additionally provided with groove, and groove can be used for that temperature measuring apparatus is fixedly mounted, can be more square
Its cooling effect is detected to face, is also fixedly connected with spoiler 11 on the side wall of 2 inner cavity of turbo blade main body, spoiler 11 and is disturbed
There are four the interval of spoiler 11 setting on stream rib 13, cold air inlet 7 and cold air outlet 8 are all provided with, and cold air inlet 7 and cold air go out
For mouth 8 not in same perpendicular, the tip of trailing edge 6 also is provided with cooling duct 12, and spoiler 11 is circular slab.
When in use, heat is flowed through and absorbs in the through-hole that cold air passes through laminate 15, then in the gas of blade back 4 and leaf basin 5
Fenestra 9 cools down its surface, and a portion is flowed out by air film hole 9, can form one layer of cold air on the surface of blade
Thin layer effectively protects the outer surface of blade, meanwhile, cold air is carried out in cooling chamber 10 by cold air inlet 7, by disturbing
The collective effect of flowing plate 11 and flow-disturbing rib 13 improves entire heat transfer process and efficiency, then cold air outlet 8 and trailing edge 6 from top
The cooling duct 12 at place is discharged, the temperature for making entire turbo blade main body 2 that material be kept to can bear.
It can to sum up obtain, the utility model makes cold air in the form of impinging cooling by the air film hole 9 in blade back 4 and leaf basin 5
The surface of blade back 4 and leaf basin 5 is cooled down, and a part is flowed out by air film hole 9, can form one layer on the surface of blade
Cold air thin layer effectively protects the outer surface of blade, meanwhile, the inner cavity of inner vanes is equipped with spoiler 11 and flow-disturbing rib
13, enhance the efficiency of internal heat, improves the cooling effect of entire blade.On the other hand, the laminate 15 that the utility model passes through,
Cold air flows through in the through-hole of laminate 15 and absorbs heat, can not only reduce the consumption of air, while heat exchange area is big, and
Good cooling results, in addition, the exchange capability of heat of entire spoiler 11 can be improved, further by the way that spoiler 11 is set as round
Reinforce the cooling performance of entire blade interior, whole device is compact-sized, is rationally and effectively compounded with a variety of cooling provisions, makes whole
The cooling effect of a blade is more preferable.
It should be noted that, in this document, relational terms such as first and second and the like are used merely to a reality
Body or operation are distinguished with another entity or operation, are deposited without necessarily requiring or implying between these entities or operation
In any actual relationship or order or sequence.Moreover, the terms "include", "comprise" or its any other variant are intended to
Non-exclusive inclusion, so that the process, method, article or equipment including a series of elements is not only wanted including those
Element, but also including other elements that are not explicitly listed, or further include for this process, method, article or equipment
Intrinsic element.In the absence of more restrictions, the element limited by sentence " including a reference structure ", is not arranged
Except there is also other identical elements in the process, method, article or apparatus that includes the element.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is understood that these embodiments can be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaired
Change, replacement and variant, the scope of the utility model is defined by the appended claims and the equivalents thereof.
Claims (6)
1. a kind of aero engine turbine blades with refrigerating function, including wheel disk of turbine (1), turbo blade main body (2) and
Handle assembly (3), it is characterised in that: the turbo blade main body (2) is uniformly mounted on the outside of wheel disk of turbine (1), the handle
Parts (3) are welded on the bottom of turbo blade main body (2)；
The turbo blade main body (2) includes blade back (4), leaf basin (5), trailing edge (6), cold air inlet (7), cold air outlet (8), gas
Fenestra (9), cooling chamber (10), spoiler (11), cooling duct (12) and flow-disturbing rib (13), the blade back (4) are arranged in turbine
The outside of blade body (2), in the inside of turbo blade main body (2), the trailing edge (6) is arranged in whirlpool for leaf basin (5) setting
The top of impeller blade main body (2), the cold air inlet (7) are provided with the bottom of turbo blade main body (2), the cold air outlet
(8) it is provided with the top of turbo blade main body (2), the air film hole (9) is provided with the outer surface of blade back (4), the cooling chamber
(10) it is arranged in the inner cavity of turbo blade main body (2), the top of the flow-disturbing rib (13) is fixedly welded on turbo blade main body (2)
Inner cavity top, the cooling duct (12) is mounted on the inside of cooling chamber (10), the fixed weldering in one end of the spoiler (11)
Connect the outside in flow-disturbing rib (13)；
The handle assembly (3) includes hub lumen (301), flank (302), dovetail (303), link block (304), airflow channel
(305) and bottom plate (306), the bottom plate (306) are fixedly welded on the bottom of turbo blade main body (2), and the flank (302) is solid
Surely the two sides of bottom plate (306) are connected to, the hub lumen (301) is provided with the bottom of bottom plate (306), the link block (304)
It is fixedly welded on the inside of hub lumen (301), the airflow channel (305) is provided with the outside of link block (304), and one end connects
It passes to cold air inlet (7), the dovetail (303) is fixedly welded on the bottom of link block (304).
2. a kind of aero engine turbine blades with refrigerating function according to claim 1, it is characterised in that: described
Blade back (4) and leaf basin (5) include substrate (14) and laminate (15), and the inside of the laminate (15) is uniformly provided with channel.
3. a kind of aero engine turbine blades with refrigerating function according to claim 1, it is characterised in that: described
The surface of leaf basin (5) also is provided with air film hole (9), and the two sides of the air film hole (9) are additionally provided with groove.
4. a kind of aero engine turbine blades with refrigerating function according to claim 1, it is characterised in that: described
It is also fixedly connected with spoiler (11) on the side wall of turbo blade main body (2) inner cavity, the spoiler (11) and flow-disturbing rib (13)
On spoiler (11) be spaced setting.
5. a kind of aero engine turbine blades with refrigerating function according to claim 1, it is characterised in that: described
There are four cold air inlet (7) and cold air outlet (8) are all provided with, and cold air inlet (7) and cold air outlet (8) be not in same perpendicular
It is interior.
6. a kind of aero engine turbine blades with refrigerating function according to claim 1, it is characterised in that: described
The tip of trailing edge (6) also is provided with cooling duct (12), and the spoiler (11) is circular slab.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821983882.8U CN209040894U (en) | 2018-11-28 | 2018-11-28 | A kind of aero engine turbine blades with refrigerating function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821983882.8U CN209040894U (en) | 2018-11-28 | 2018-11-28 | A kind of aero engine turbine blades with refrigerating function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209040894U true CN209040894U (en) | 2019-06-28 |
Family
ID=67043809
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821983882.8U Expired - Fee Related CN209040894U (en) | 2018-11-28 | 2018-11-28 | A kind of aero engine turbine blades with refrigerating function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209040894U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112459849A (en) * | 2020-10-27 | 2021-03-09 | 哈尔滨广瀚燃气轮机有限公司 | Cooling structure for turbine blade of gas turbine |
| CN112648018A (en) * | 2020-12-01 | 2021-04-13 | 日照黎阳工业装备有限公司 | High-temperature alloy blade for engine capable of ensuring efficient cooling of front edge of blade |
| CN114017131A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳发动机研究所 | Become half plywood cooling structure of how much low pressure turbine guide vane |
| CN114109514A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Turbine blade pressure surface cooling structure |
-
2018
- 2018-11-28 CN CN201821983882.8U patent/CN209040894U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112459849A (en) * | 2020-10-27 | 2021-03-09 | 哈尔滨广瀚燃气轮机有限公司 | Cooling structure for turbine blade of gas turbine |
| CN112648018A (en) * | 2020-12-01 | 2021-04-13 | 日照黎阳工业装备有限公司 | High-temperature alloy blade for engine capable of ensuring efficient cooling of front edge of blade |
| CN114017131A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳发动机研究所 | Become half plywood cooling structure of how much low pressure turbine guide vane |
| CN114109514A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Turbine blade pressure surface cooling structure |
| CN114017131B (en) * | 2021-11-12 | 2023-06-02 | 中国航发沈阳发动机研究所 | Variable geometry low pressure turbine guide vane half-layer plate cooling structure |
| CN114109514B (en) * | 2021-11-12 | 2023-11-28 | 中国航发沈阳发动机研究所 | Turbine blade pressure surface cooling structure |
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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: 20190628 Termination date: 20211128 |