CN206360726U - A kind of air film hole of efficient air cooling turbine rotor blade - Google Patents
A kind of air film hole of efficient air cooling turbine rotor blade Download PDFInfo
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- CN206360726U CN206360726U CN201621408690.5U CN201621408690U CN206360726U CN 206360726 U CN206360726 U CN 206360726U CN 201621408690 U CN201621408690 U CN 201621408690U CN 206360726 U CN206360726 U CN 206360726U
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- blade
- film hole
- air film
- turbine rotor
- air
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Abstract
A kind of air film hole of efficient air cooling turbine rotor blade, air film hole (5) is located on blade (1), the air film hole (5) is circle in the aperture of blade (1) inner chamber, it is ellipse in the aperture of blade (1) outer surface, the oval major axis and short axle are all higher than the circular diameter, and the circular center of circle and the oval central point are coaxial.
Description
Technical field:Aero engine turbine blades, are related to a kind of air film hole of efficient air cooling turbine rotor blade.
Background technology：
To adapt to demand of the Fighting Planes of future generation to engine, it is desirable to which engine greatly improves its thrust-weight ratio, this
Temperature before engine turbine certainly will be caused further to raise.Therefore, the temperature capability of turbo blade how is improved, is to solve turbine
One important measures of preceding temperature.
At present, aero-turbine rotor blade is typically using the higher single crystal high-temperature alloy material of temperature resistance ability or elder generation
Enter Cooling Design technology, to meet the elevated requirement of turbine part temperature.However, merely using the higher monocrystalline high temperature material of heatproof
Material, reduction temperature amplitude is low, scope is small, it is difficult to meet design requirement.When using efficient air cooling structure, film hole structure turns into
Design core；And existing air film hole generally use cylindrical structure, it easily causes to penetrate outside cold air, blade film overcast effect compared with
Difference, cooling effectiveness is extremely low, and air film hole inwall has step and crest line, and manufacturability is poor.
Utility model content：
The purpose of utility model：In order to reduce the operating temperature of turbine blade surface parent metal, blade surface is improved
Temperature capability and cooling effectiveness, can be effective the utility model proposes a kind of film hole structure of efficient air cooling turbine rotor blade
Film overcast effect is improved, strengthens the surface temperature capability of blade.
The technical solution of the utility model：
A kind of air film hole of efficient air cooling turbine rotor blade, air film hole 5 is located on blade 1, and the air film hole 5 is in blade
The aperture of 1 inner chamber is circle, is ellipse in the aperture of the outer surface of blade 1, the oval major axis and short axle are all higher than institute
The diameter of circle is stated, the circular center of circle and the oval central point are coaxial.
Beneficial effect：
Rationalization's distribution of cold air flow, improves blade film overcast effect；Hold warm energy in the surface of enhancing blade
Power, improves the cooling effectiveness of blade；It is simple and compact for structure, good manufacturability, steady quality.
Brief description of the drawings：
The efficient air cooling turbine rotor blade schematic diagrames of Fig. 1；
Fig. 2 blade air film hole schematic cross-sections；
Fig. 3 air film hole schematic diagrames.
Embodiment：
The utility model is on the basis of the cooling scheme of turbine rotor blade inner chamber, with reference to the work of electro-stream machining air film hole
Skill advantage, carries out ellipse film hole structure design, and by changing air film hole density degree, adjusts air film orifice angle, carries out
The distribution of cold air flow, reaches improvement blade film overcast effect, the cooling effect of blade is improved, so as to form efficient air-cooled turbine
The film hole structure of rotor blade.
Blade construction in efficient air cooling turbine rotor blade air film hole of the present utility model is shown in Fig. 1, Fig. 2 and Fig. 3.It is described
Efficient air cooling turbine rotor blade by blade 1, listrium 2, stretch root 3 and tenon 4 is constituted, wherein, overall distribution air film hole on blade 1
5, the air film hole 5 is circle in the aperture of the inner chamber of blade 1, is ellipse in the aperture of the outer surface of blade 1, described oval
Major axis and short axle are all higher than the circular diameter, and the circular center of circle and the oval central point are coaxial.
The air film hole of the efficient air cooling turbine rotor blade is circle in the aperture of the inner chamber of blade 1, in the outer surface of blade 1
Aperture is ellipse, by the shape to film hole structure, size design, blade profile is surrounded by cold air, and one layer of formation is cold
Gas shielded film, then again by the adjustment to air film hole density, angle, makes blade temperature field in interior adjustment in a big way, so that
The distribution of rationalization's cold air flow, improves blade film overcast effect, improves the cooling effectiveness of blade.It is this simple in construction tight
Gather, good manufacturability, steady quality is more beneficial for cold air flow, reduces flow resistance, and the cooling to blade surface matrix material can be achieved
Protection, can meet Practical Project use requirement.
Claims (1)
1. a kind of air film hole of efficient air cooling turbine rotor blade, it is characterised in that air film hole (5) is located on blade (1), described
Air film hole (5) is circle in the aperture of blade (1) inner chamber, is ellipse in the aperture of blade (1) outer surface, described oval
Major axis and short axle are all higher than the circular diameter, and the circular center of circle and the oval central point are coaxial.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621408690.5U CN206360726U (en) | 2016-12-21 | 2016-12-21 | A kind of air film hole of efficient air cooling turbine rotor blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621408690.5U CN206360726U (en) | 2016-12-21 | 2016-12-21 | A kind of air film hole of efficient air cooling turbine rotor blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206360726U true CN206360726U (en) | 2017-07-28 |
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ID=59374040
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621408690.5U Active CN206360726U (en) | 2016-12-21 | 2016-12-21 | A kind of air film hole of efficient air cooling turbine rotor blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206360726U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109307577A (en) * | 2018-08-24 | 2019-02-05 | 北京航空航天大学 | A kind of air-cooling apparatus for high-temperature vibrating test |
| CN109613027A (en) * | 2018-11-29 | 2019-04-12 | 中国航发沈阳黎明航空发动机有限责任公司 | To the process unit and method of turbo blade leading edge air film hole X-ray detection |
-
2016
- 2016-12-21 CN CN201621408690.5U patent/CN206360726U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109307577A (en) * | 2018-08-24 | 2019-02-05 | 北京航空航天大学 | A kind of air-cooling apparatus for high-temperature vibrating test |
| CN109613027A (en) * | 2018-11-29 | 2019-04-12 | 中国航发沈阳黎明航空发动机有限责任公司 | To the process unit and method of turbo blade leading edge air film hole X-ray detection |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 610500 Xindu Xuefu Road, Xindu District, Chengdu, Sichuan Patentee after: AECC SICHUAN GAS TURBINE Research Institute Address before: 621703 P.O. Box 305, Mianyang City, Sichuan Province Patentee before: CHINA GAS TURBINE EST |
|
| CP03 | Change of name, title or address |