Bleed air cooling structure and aeroengine with bleed air cooling structure

An aero-engine and air-cooling technology, which is used in engine components, engine cooling, turbine/propulsion cooling, etc., can solve problems affecting the safety and reliability of engines and aircraft, and achieve the benefits of assembly and adjustment, prolong service life, The effect of reducing the operating temperature

Active Publication Date: 2016-08-24
CHINA HANGFA SOUTH IND CO LTD
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The invention provides a bleed air cooling structure and an aero-engine with the bleed air cooling structure to solve the technical problem that the existing aero-engine turbine components are overheated due to untimely cooling and affect the safety and reliability of the engine and aircraft

Method used

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  • Bleed air cooling structure and aeroengine with bleed air cooling structure
  • Bleed air cooling structure and aeroengine with bleed air cooling structure
  • Bleed air cooling structure and aeroengine with bleed air cooling structure

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Embodiment Construction

[0042] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0043] Aiming at the technical problem that the existing aero-engine turbine components are overheated due to untimely cooling, which affects the safety and reliability of the engine and aircraft, this embodiment provides an engine bleed air cooling structure, which is used to reduce the outer surface of the turbine components. Working temperature, prevent the heat transfer of turbine components to the aircraft, and ensure the reliability and safety of the engine. refer to figure 1 , The bleed air cooling structure provided in this preferred embodiment includes: a left bleed hood 1 and a right bleed hood 2 designed in half. Preferably, the left bleed hood 1 and the right bleed hood 2 are conn...

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Abstract

The invention discloses a bleed air cooling structure and an aeroengine with the bleed air cooling structure. The bleed air cooling structure comprises a left bleed air hood and a right bleed air hood, wherein the left bleed air hood and the right bleed air hood are designed in a half-and-half structure; the left bleed air hood comprises a first outer hood, a first inner hood, a first middle support belt and a first rear hood; the right bleed air hood comprises a second outer hood, a second inner hood, a second middle support belt and a second rear hood; a mounting base which is used for fixedly installing a thermocouple conversion seat, an open hole which is used for temperature detection of a thermocouple probe and a through hole which is used for an exhaust pipe/oil mist pipe to pass through are arranged on and formed in the first rear hood and/or the second rear hood; a first bleed air seat and a second bleed air seat which are used for cooling the outer surface of a turbine component is arranged on the first outer hood and/or the second outer hood. According to the bleed air cooling structure, overtemperature of the engine is effectively avoided, and high temperature of the engine is prevented from being transferred to an airplane, thereby prolonging the service life of the engine and the airplane.

Description

technical field [0001] The invention relates to the field of aeroengines, in particular to an bleed air cooling structure and an aeroengine with the bleed air cooling structure. Background technique [0002] In a turboprop engine, the turbine components are in a high-temperature and high-speed environment. During the working process of the engine, the maximum temperature of the turbine can reach 1160K. The heat of the components is transferred to the aircraft, and it is necessary to properly cool the turbine components to ensure the safety and reliability of the engine and the aircraft. Therefore, it is urgent to design a bleed air cooling structure for aero-engines. Contents of the invention [0003] The invention provides a bleed air cooling structure and an aero-engine with the bleed air cooling structure, in order to solve the technical problem that the existing aero-engine turbine components are overheated due to untimely cooling and affect the safety and reliability ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/18
CPCF02C7/18
Inventor 倪慧妍杨春华
Owner CHINA HANGFA SOUTH IND CO LTD
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