CN209129676U - A kind of air-cooled turbine rotor blade - Google Patents
A kind of air-cooled turbine rotor blade Download PDFInfo
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- CN209129676U CN209129676U CN201822104315.7U CN201822104315U CN209129676U CN 209129676 U CN209129676 U CN 209129676U CN 201822104315 U CN201822104315 U CN 201822104315U CN 209129676 U CN209129676 U CN 209129676U
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Abstract
This application discloses a kind of air-cooled turbine rotor blades, the air-cooled turbine rotor blade includes blade, the blade is cavity structure, space lattice body is equipped in it, blade surface is distributed with along rotor blade radial direction splits seam and multiple air film holes, the radial passage for being connected to the cavity structure is equipped at the blade root of blade, cooling air-flow flows into from radial passage, splits seam and air film hole outflow certainly to reduce the temperature of the air-cooled turbine rotor blade.The air-cooled turbine rotor blade of the application significantly increases the area of turbine rotor blade internal heat due to the presence of space lattice body, enhances the cooling effect of turbine rotor blade, and the wall surface temperature of blade can be effectively reduced；In addition, also reducing constraint of the cooling structure in turbine rotor blade to pneumatic modelling, it is advantageously implemented the high efficiency of turbine.
Description
Technical field
The application belongs to gas-turbine unit field, in particular to a kind of cooling blade of air-cooled turbine.
Background technique
Gas-turbine unit is usually made of compressor, combustion chamber and the big component of turbine three, and turbine part fires high temperature
The interior of gas can be converted into mechanical energy.The turbo blade needs of gas-turbine unit are held in working under the gas condition of high temperature
Gas-turbine unit is determined by the temperature capability of the temperature far more than matrix material melting point, first order turbine rotor blade
Turbine inlet temperature.For the use problem for improving turbo blade, need to draw the lower high pressure of temperature from compressor under normal conditions
Air enters the cavity of blade, and pressure-air cools down turbo blade as cooling air.
In the prior art, as shown in Figure 1, turbine rotor blade includes tenon 1, listrium 2, blade 3 and blade tip 4, in tenon 1
1 or more radial passage 5 is arranged at bottom, and cold air is entered in blade 3 by radial passage 5 to be cooled down.As shown in Fig. 2, turbine turns
The blade 3 of blades is cavity structure, and blade 3 can be divided into leading edge 8, exhaust side 9, leaf basin 6 and blade back 7 by region.According to turbine
The difference of the thermic load of rotor blade wall surface different zones, the cooling that multiple revolutions can be generally designed in the cavity of blade 3 are logical
Road 10, cold air are passed through 3 inner cavity of blade blade by radial passage 5 and are cooled down.It is usually used in order to obtain better cooling effect
Compound cooling mode carries out turbine rotor blade effectively cooling comprising is arranged in leading edge 8 multiple rows of along blade radial height point
What the air film hole 12 of cloth and exhaust side 9 were arranged splits seam 1, and flow-disturbing rib or turbulence columns etc. is arranged in cooling duct 10, keeps leaf with this
Piece wall surface temperature is in use scope and uniform as far as possible.But due to the presence of rotating channel 10, for the cooling for meeting each channel
The demand of circulation area, blade 3 and blade tip 4 inevitably increased section thickness, affect the pneumatic of turbine rotor blade
Moulding, and turbine rotor blade weight is increased, higher tenon and wheel disc load are brought, turbine rotor blade is drawn
At blade root the problem of intensity.
Summary of the invention
The purpose of the application is any of the above-described to solve the problems, such as there is provided a kind of air-cooled turbine rotor blade.
The technical solution of the application is: a kind of air-cooled turbine rotor blade, the air-cooled turbine rotor blade includes blade,
The blade is cavity structure, and interior to be equipped with space lattice body, blade surface is distributed with along rotor blade radial direction and splits seam
With multiple air film holes, the radial passage for being connected to the cavity structure is equipped at the blade root of blade, cooling air-flow is flowed from radial passage
Enter, split seam and air film hole outflow certainly to reduce the temperature of the air-cooled turbine rotor blade.
In this application, the blade and radial cross-sections surfaces include leading edge, leaf basin, blade back and are vented side, described to split
It seams and sets on exhaust side, on the air film hole is distributed at leading edge, leaf basin and blade back 7 at least one.
In this application, the space lattice body is made of the body of rod and node, and the body of rod is connected to the node and constitutes
Space lattice body.
In this application, the space lattice body includes four sides grid body, square net body and hexagon grid body
One of.
In this application, the space lattice body and the blade integrated molding.
In this application, the integrated molding includes 3D printing and casting.
The air-cooled turbine rotor blade of the application is significantly increased in turbine rotor blade due to the presence of space lattice body
The area of portion's heat exchange, enhances the cooling effect of turbine rotor blade, the wall surface temperature of blade can be effectively reduced；In addition, also
Constraint of the cooling structure in turbine rotor blade to pneumatic modelling is reduced, the high efficiency of turbine is advantageously implemented.The application
In space lattice body on the one hand there is good intensity and rigidity, can leading edge, leaf basin, blade back and exhaust side shape to blade
At effective support, it can also avoid selecting thicker blade profile, and simplify the cooling structure of blade inner cavity, avoid using complexity
Rotating channel, the overall weight of blade can be significantly reduced, to reduce the centrifugal load of blade tenon and wheel disc, improve leaf
The reliability of piece.
Detailed description of the invention
In order to illustrate more clearly of technical solution provided by the present application, attached drawing will be briefly described below.It is aobvious and easy
Insight, drawings discussed below are only some embodiments of the present application.
Fig. 1 is turbine rotor blade structure diagram；
Fig. 2 is the turbine rotor blade cross-sectional of existing cooling structure；
Fig. 3 is the turbine rotor blade cross-sectional of the application；
Fig. 4 (a) is the basic unit of positive tetrahedron space lattice body in the application；
Fig. 4 (b) is the basic unit of square space lattice body in the application；
Fig. 4 (c) is the basic unit of hexagonal prisms space lattice body in the application.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.
The application's is designed to provide a kind of air-cooled turbine rotor blade, the installation space grid body 13 in blade inner cavity,
While realizing efficiently cooling, the weight of blade is reduced, to reduce the load of blade tenon and the turbine disk.
The air-cooled turbine rotor blade of the application has and the same or similar knot of turbine rotor blade in the prior art
Structure, the air-cooled turbine rotor blade of the application include tenon 1, listrium 2, blade 3 and blade tip 4, the bottom of tenon 1 have 1 with
On radial passage 5, blade 3 is cavity structure, and blade 3 can be divided into leading edge 8, exhaust side 9, leaf basin 6 and blade back 7 by region, cold
But air is passed through 3 inner cavity of blade of turbine rotor blade by the radial passage 5 of 1 bottom of tenon, is arranged in inner cavity 3 intensive uniformly distributed
Space lattice body 13, instead of the rotating channel 10 generallyd use in the prior art, space lattice body 13 and 3 inner wall of blade
Connection.It, can be according to the load condition that exchanges heat outside blade, arrangement one in the leading edge 8 of turbine rotor blade, leaf basin 6,7 region of blade back
Row or multiple rows of air film hole 12 arrange that a row is radially-arranged on exhaust side 9 and split seam 11.Cooling air can be flowed from radial passage 5
Enter, from air film hole 12 and splits 11 outflow of seam.
In the application in embodiment, the basic unit of space lattice body 13 can be positive tetrahedron, square, six ribs
Column or other steric configurations.In basic unit, space lattice body 13 is made of the body of rod 14 and node 15, and the body of rod 14 is in node 15
Junction be spherical shape, with the connection of the body of rod 14 between two nodes 15.
In the application in embodiment, 3 integrated molding of space lattice body 13 and blade, forming technique can use example
Such as 3D printing or casting.
Under working condition, conducted by the heat that sprue high-temperature fuel gas is passed to blade outside wall surface to space lattice body 13, with
Heat exchange occurs for cooling air, and the cooled air of heat is taken away, and by air film hole 12 or splits 11 discharge turbine rotor blades of seam,
Also, after turbine rotor blade is discharged in cooling air, it can also be formed and be covered on turbine rotor blade surface, further fire high temperature
The outside wall surface of gas and turbine rotor blade separates, and heat transfer of the high-temperature fuel gas to blade 3 is reduced, thus effectively to turbine rotor leaf
Piece is cooled down.
The air-cooled turbine rotor blade of the application significantly increases turbine rotor blade due to the presence of space lattice body 13
The area of internal heat enhances the cooling effect of turbine rotor blade, and the wall surface temperature of turbine rotor blade can be effectively reduced
Degree, additionally reduces constraint of the cooling structure to pneumatic modelling of turbine rotor blade, is advantageously implemented the high efficiency of turbine.
13 one side of space lattice body in the application has good intensity and rigidity, can leading edge 8 to blade 3, leaf basin 6, leaf
Back 7 and exhaust side 9 form effective support, in addition it can avoid selecting thicker blade profile, simplify in turbine rotor blade
The cooling structure of chamber avoids the overall weight of turbine rotor blade being significantly reduced, to reduce using complicated rotating channel
The centrifugal load of blade tenon and wheel disc improves the reliability of blade.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (6)
1. a kind of air-cooled turbine rotor blade, which is characterized in that the air-cooled turbine rotor blade includes blade (3), the leaf
Body (3) is cavity structure, and interior to be equipped with space lattice body (13), blade surface is distributed with along rotor blade radial direction and splits seam
(11) and multiple air film holes (12), be equipped with the radial passage for being connected to the cavity structure at the blade root of blade (3), cooling air-flow from
Radial passage flows into, splits seam (11) and air film hole (12) outflow certainly to reduce the temperature of the air-cooled turbine rotor blade.
2. air-cooled turbine rotor blade as described in claim 1, which is characterized in that the blade (3) and radial section table
Face includes leading edge (8), leaf basin (6), blade back (7) and exhaust side (9), and described split seam (11) are arranged in exhaust side (9), the air film
On hole (12) is distributed at leading edge (8), leaf basin (6) and blade back (7) at least one.
3. air-cooled turbine rotor blade as claimed in claim 1 or 2, which is characterized in that the space lattice body (13) is by bar
Body (14) and node (15) are constituted, and the body of rod (14) is connected to the node (15) and constitutes space lattice body (13).
4. air-cooled turbine rotor blade as claimed in claim 3, which is characterized in that the space lattice body (13) includes four sides
One of grid body, square net body and hexagon grid body.
5. air-cooled turbine rotor blade as described in claim 1, which is characterized in that the space lattice body (13) and the leaf
Body (3) integrated molding.
6. air-cooled turbine rotor blade as claimed in claim 5, which is characterized in that the integrated molding include 3D printing and
Casting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822104315.7U CN209129676U (en) | 2018-12-14 | 2018-12-14 | A kind of air-cooled turbine rotor blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822104315.7U CN209129676U (en) | 2018-12-14 | 2018-12-14 | A kind of air-cooled turbine rotor blade |
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| Publication Number | Publication Date |
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| CN209129676U true CN209129676U (en) | 2019-07-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201822104315.7U Active CN209129676U (en) | 2018-12-14 | 2018-12-14 | A kind of air-cooled turbine rotor blade |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111636925A (en) * | 2020-06-08 | 2020-09-08 | 清华大学 | Turbine rotor blade and turbomachine with same |
| CN111677557A (en) * | 2020-06-08 | 2020-09-18 | 清华大学 | Turbine guide blade and turbo machine with same |
| CN112610285A (en) * | 2020-12-18 | 2021-04-06 | 武汉大学 | Hollow quiet leaf of imitative diamond cell topology's steam turbine strengthens dehumidification structure and steam turbine dehydrating unit |
| CN113901613A (en) * | 2021-10-20 | 2022-01-07 | 中国航发沈阳黎明航空发动机有限责任公司 | Design method of rotor shock absorber with cooling structure |
| CN113944515A (en) * | 2021-10-20 | 2022-01-18 | 中国航发四川燃气涡轮研究院 | Turbine blade with cooled front edge split |
| CN114151139A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Method for simulating flow of air film hole cold air layer on surface of turbine blade by adopting permeation model |
-
2018
- 2018-12-14 CN CN201822104315.7U patent/CN209129676U/en active Active
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111636925A (en) * | 2020-06-08 | 2020-09-08 | 清华大学 | Turbine rotor blade and turbomachine with same |
| CN111677557A (en) * | 2020-06-08 | 2020-09-18 | 清华大学 | Turbine guide blade and turbo machine with same |
| CN111677557B (en) * | 2020-06-08 | 2021-10-26 | 清华大学 | Turbine guide blade and turbo machine with same |
| CN112610285A (en) * | 2020-12-18 | 2021-04-06 | 武汉大学 | Hollow quiet leaf of imitative diamond cell topology's steam turbine strengthens dehumidification structure and steam turbine dehydrating unit |
| CN112610285B (en) * | 2020-12-18 | 2021-09-14 | 武汉大学 | Hollow quiet leaf of imitative diamond cell topology's steam turbine strengthens dehumidification structure and steam turbine dehydrating unit |
| CN113901613A (en) * | 2021-10-20 | 2022-01-07 | 中国航发沈阳黎明航空发动机有限责任公司 | Design method of rotor shock absorber with cooling structure |
| CN113944515A (en) * | 2021-10-20 | 2022-01-18 | 中国航发四川燃气涡轮研究院 | Turbine blade with cooled front edge split |
| CN114151139A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Method for simulating flow of air film hole cold air layer on surface of turbine blade by adopting permeation model |
| CN114151139B (en) * | 2021-10-20 | 2023-09-19 | 中国航发四川燃气涡轮研究院 | Method for simulating cold air layer flow of air film holes on surface of turbine blade by adopting permeation model |
| CN113901613B (en) * | 2021-10-20 | 2024-04-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Design method of rotor damper with cooling structure |
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