Combined cooling structure for turbine blade middle-part porous impact aerating film

A technology of turbine blades and cooling structure, which is applied to the supporting elements of blades, engine elements, machines/engines, etc., can solve the problem of insufficient cooling of blades, and achieve the effect of improving heat exchange, reducing flow resistance and improving cooling.

Inactive Publication Date: 2008-02-20
BEIHANG UNIV
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  • Abstract
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AI Technical Summary

Problems solved by technology

Most of the conventional turbine blades currently designed are arranged with ribs of various shapes inside the blades to increase the internal disturbance and improve the heat transfer effect, and some air film holes with small diameters are often arranged on the outer surface of the blades. , forming full air film coverage, the cooling effect of turbine blades designed in this way is generally around 0.5, with the increase of gas temperature in front of the turbine, such cooling effect is obviously not enough for blade cooling, so efficient The invention of the turbine cooling structure is very important and urgent

Method used

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  • Combined cooling structure for turbine blade middle-part porous impact aerating film
  • Combined cooling structure for turbine blade middle-part porous impact aerating film

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Embodiment Construction

[0013] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0014] As shown in Fig. 1, the present invention is a combined cooling structure of a porous impingement air-entraining film applied to the middle part of an aeroengine turbine blade, which includes: air film holes and impact holes, characterized in that: arranged on the outer surface of the blade Air film holes with a diameter of 1.0mm to 1.5mm, the number of each exhaust film hole in the span direction is 10 to 15, and the impact holes equivalent to twice the number of air film holes are arranged in the downstream area of ​​the air film holes inside the blade , the diameter of the impact hole is 0.6mm~08mm, the impact hole is arranged in the range of 7~10 times the diameter of the impact hole downstream of the corresponding air film hole, and is located between the two air film holes, the impact holes are arranged in a staggered manner, and the adjacent The...

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Abstract

The invention discloses a multi-hole impact and air film combination cooling structure used at the middle of the turbine blades of an aeroengine. The cooling structure is that: air film holes with the diameter of 1.0 mm-1.5 mm are arranged on the outer surface of the blade, the amount of the air film holes at each extension direction is 10-20, inclined impact holes are arranged inside the blades in the downstream area of the air film holes, the amount of the inclined impact holes doubles that of the air film holes. A highly cooling area with the large area is formed inside the blades through the impact holes; at the same times, the air film holes outside the blades form an air film protection area to jointly realize the blade-cooling purpose. The results of the model test and the three-dimensional numerical simulation indicate that the cooling effect of the blades can reach 0.7 at least; at the same time, the pneumatic loss can be reduced distinctly and the flow resistance is distinctly lower than the ordinary turbine blades owing to the characteristic of cooling structure.

Description

technical field [0001] The invention relates to a combined cooling structure of a porous impingement air-entraining film in the middle of a turbine blade. The cooling structure is mainly used in the middle of the turbine blade of an aeroengine, and can produce a cooling effect of more than 0.7 to meet the cooling requirements of the turbine blade of the aeroengine. Background technique [0002] The most important performance index of an engine is the thrust-to-weight ratio. As people's performance requirements for the engine continue to increase, so do the requirements for the thrust-to-weight ratio. The most effective means to improve the thrust-to-weight ratio of the engine is to increase the gas temperature in front of the turbine. The pre-researched thrust-to-weight ratio 10 aero-engine before the turbine temperature is about 1850K ~ 1950K. However, the various materials currently used can only maintain their high strength indicators at about 1300 °C without cooling. W...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
Inventor 陶智丁水汀徐国强孙纪宁吕品吴宏伟
Owner BEIHANG UNIV
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