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Hot gas anti-icing structure of forward-sloped engine support plate

An engine and hot gas technology, which is applied to machines/engines, mechanical equipment, jet propulsion devices, etc., can solve the problems of low thermal conductivity, increased demand for compressor anti-icing hot gas, restricting engine performance, etc., to reduce the amount of bleed air and Bleed air temperature, improved anti-icing effect, reduced engine weight

Active Publication Date: 2018-08-24
BEIHANG UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Compared with metal materials, composite materials have low thermal conductivity and anisotropy. If the traditional metal parts are simply used in the design of hot gas anti-icing, it will inevitably increase the demand for anti-icing hot gas from the compressor, which will restrict the improvement of engine performance.

Method used

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  • Hot gas anti-icing structure of forward-sloped engine support plate
  • Hot gas anti-icing structure of forward-sloped engine support plate
  • Hot gas anti-icing structure of forward-sloped engine support plate

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0029] The opening angle of the gas film seam of the support plate used in the test points to the direction of the front edge, its structural parameters are shown in Table 1, and its shape structure is as follows figure 1 and image 3 shown.

[0030] Table 1 Basic structural parameters of composite struts

[0031] Leading edge thickness δ

Gas film slit width l

Impact hole distance s

Gas film slit length b

Impact distance Zn

Impact aperture d h

[0032] The slit angle of the air film seam has a significant impact on the anti-icing characteristics of the support plate, including the air film heating characteristics of the outer wall surface, the water droplet impact characteristics of the outer wall surface, and the impact heat transfer characteristics of the inner leading edge wall surface.

[0033] In order to preliminarily explore the mechanism of the influence of hot air film on the anti-icing characteristics of struts, the Euler me...

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Abstract

The invention discloses a forward-gap hot-gas anti-icing structure with a supporting plate for an engine, is suitable for the anti-icing structural design of aero-engine front-edge parts, and belong to the field of icing prevention for aero-engines. The forward-gap hot-air anti-icing structure comprises a composite material blade base body and a flute tube, and is characterized in that the blade base body is made from a composite material, air film gaps are inclined forwards, and the wall surfaces of the air film gaps are tangent with a hot-air impact wall surface. The forward-gap hot-air anti-icing structure makes the best of the advantage of jet impingement heat transfer, can improve the hot-air anti-icing effect of a guiding blade of the engine, and reduces the air entraining content and the induced air temperature of the engine, meanwhile, the weight of the engine can be reduced, and improvement of the performance, the security and the economy of the aero-engine are facilitated.

Description

technical field [0001] The invention relates to a hot gas anti-icing structure of a forward-sloped engine support plate, which is suitable for the design of the anti-icing structure of the leading edge parts of the aero-engine, and belongs to the field of anti-icing of the aero-engine. Background technique [0002] Aeroengines will freeze under icing weather conditions. The icing of the air intake components at the leading edge of the engine will have a great impact on the engine, which will reduce the engine power and cause engine damage in severe cases. At present, my country's national military standards and airworthiness regulations have put forward certain design requirements for turbofan engine anti-icing. [0003] Aircraft icing has always been an important issue affecting flight safety, and engine inlet icing is also a serious hazard. Due to the above-mentioned advantages of composite materials, coupled with the requirements of engine thrust-to-weight ratio design g...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/047
CPCF02C7/047
Inventor 柯鹏张韵蒋家庆杨春信陆海鹰李云单
Owner BEIHANG UNIV
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