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Aircraft engine high-pressure turbine guide vane with liquid-state metal active cooling function

A high-pressure turbine and liquid metal technology, which is applied to engine components, machines/engines, mechanical equipment, etc., can solve problems that are not suitable for the cooling of aeroengine guide vanes

Active Publication Date: 2018-11-16
AERO ENGINE ACAD OF CHINA
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Problems solved by technology

However, due to the difference in aerodynamic layout and the harsh requirements of aero-engines on space and weight, this solution is not suitable for the cooling of aero-engine guide vanes. Therefore, how to apply liquid metal cooling technology to aerospace engines has become a necessary research direction

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  • Aircraft engine high-pressure turbine guide vane with liquid-state metal active cooling function
  • Aircraft engine high-pressure turbine guide vane with liquid-state metal active cooling function
  • Aircraft engine high-pressure turbine guide vane with liquid-state metal active cooling function

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Embodiment Construction

[0024] The present disclosure will be further described in detail below with reference to the drawings and embodiments. It can be understood that the specific implementation manners described here are only used to explain relevant content, rather than to limit the present disclosure. It should also be noted that, for ease of description, only parts related to the present disclosure are shown in the drawings.

[0025] It should be noted that, in the case of no conflict, the implementation modes and the features in the implementation modes in the present disclosure can be combined with each other. The following will refer to the attached Figures 1 to 4 The present disclosure will be described in detail in combination with embodiments.

[0026] In a turbofan engine, the guide vane refers to the guide vane in the turbine blade, also called the stator vane, which is located in front of the rotor blade 700. It is rectified, and finally produces an angle that more effectively hit...

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Abstract

The invention discloses an aircraft engine high-pressure turbine guide vane with the liquid-state metal active cooling function. The aircraft engine high-pressure turbine guide vane comprises a guidevane heat absorbing part, a guide vane middle part and a guide vane heat release part; multiple channels allowing liquid-state metal to flow are arranged in the guide vane heat absorbing part, and communicate, through holes corresponding to the channels are formed in the guide vane middle part, the guide vane heat release part comprises multiple U-shaped pipelines, and the multiple U-shaped pipelines, the through holes and the channels are connected to form closed liquid-state metal flowing loops.

Description

technical field [0001] The present disclosure relates to an aeroengine high pressure turbine vane and guide with liquid metal active cooling. Background technique [0002] The high-pressure turbine components of aero-engines are subjected to extremely high heat loads during operation, and how to effectively cool them is one of the important factors restricting the development of aero-engines. [0003] The current mainstream blade cooling technology is to bleed air from the compressor outlet, and use the air to form an air film to cool the high-pressure guide vanes and high-pressure rotor blades. However, using bleed air to cool the blades will significantly affect the overall performance of the engine, such as thrust, propulsion, etc. Efficiency, etc., and with the advancement of the refined design of the turbine cooling structure, the air cooling technology is approaching the extreme, and it is difficult to make a substantial improvement. It cannot meet the increasingly hig...

Claims

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Application Information

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IPC IPC(8): F01D9/04F01D25/12
CPCF01D9/041F01D25/12
Inventor 苗辉朱江楠樊川
Owner AERO ENGINE ACAD OF CHINA
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