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Integral inertial particle separator and aero-engine based on wall bounce characteristics

An integral, separator technology, applied in the field of aero-engines, can solve the problem of low separation efficiency of particle separators, and achieve the effects of reducing particles, improving separation efficiency and improving performance

Active Publication Date: 2019-12-20
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The invention provides an integral inertial particle separator and an aero-engine based on the wall surface rebound characteristics, so as to solve the technical problem of low separation efficiency of the existing particle separators

Method used

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  • Integral inertial particle separator and aero-engine based on wall bounce characteristics
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  • Integral inertial particle separator and aero-engine based on wall bounce characteristics

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Embodiment Construction

[0032] 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.

[0033] refer to figure 1 and image 3 At present, there are mainly two types of integral particle separators used in engines. One is with pre-rotating blades and the other is without pre-rotating blades. The working principle of the integral inertial particle separator is as follows:

[0034] Particle separator with pre-rotating blades, whose blades make the air entering the flow channel of the particle separator and the foreign matter contained in it obtain circumferential velocity. Under the action of inertia, foreign objects with large mass are thrown to the outer wall of the flow path and enter the cleaning flow path to be discharged out of the machine.

[0035] Compared with the parti...

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Abstract

The invention discloses an integral inertial particle separator based on the wall surface rebounding characteristic. The integral inertial particle separator comprises an outer shell, a diverter and acentral body which are coaxially arranged from outside to inside, an air inlet channel is formed by the front half section of the central body and the front half section of the outer shell in a surrounding mode, a main flow channel is formed by the rear half section of the central body and the inner wall face of the diverter in a surrounding mode, and an eliminating flow channel is formed by therear half section of the outer shell and the outer wall face of the diverter in a surrounding mode; and the inner wall face of the outer shell is coated with a first coating, and the first coating ismade of an anti-impact energy absorption material. According to the integral inertial particle separator, the inner wall face of the outer shell is coated with the first coating made of the anti-impact energy absorption material, so that after particles entering the particle separator impact the outer shell, impact energy is absorbed by the coating, the particle rebounding speed is decreased accordingly, the particles difficultly return back to the main flow channel and are discharged out of an engine along the eliminating flow channel, and the particle separating efficiency is improved advantageously. The invention further provides an aero-engine, which comprises the integral inertial particle separator.

Description

technical field [0001] The invention relates to the field of aero-engines and particle separators, in particular to an integral inertial particle separator based on wall surface rebound characteristics. In addition, the present invention also relates to an aeroengine comprising the above-mentioned particle separator. Background technique [0002] Helicopters often need to fly in some special sandy and misty environments, such as taking off, landing and hovering in mountains, deserts, ice and snow and sea, and the working environment of the engine is becoming more and more demanding. At this time, a large amount of sand, dust, ice and snow and other foreign objects or sea salt spray are sucked into the engine. If no protective measures are taken in advance, the dust and sand will bring serious consequences to the helicopter and the engine: compressor blade abrasion and The resulting deterioration of engine performance, that is, power decline, fuel consumption rate increases,...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/05
CPCF02C7/05
Inventor 牛佳佳陈冰刘媛
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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