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Ejection type engine sand prevention system and method

An engine and ejector technology, which is used in aircraft parts, aircraft power units, and the arrangement/installation of power units to achieve the effects of small aerodynamic characteristics, compact structure and reliable sealing.

Pending Publication Date: 2020-02-28
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The traditional vortex tube sand control device is limited by the engine intake structure and installation, and cannot be integrated with the helicopter shape. The sand control device protrudes from the helicopter and creates flight resistance

Method used

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  • Ejection type engine sand prevention system and method
  • Ejection type engine sand prevention system and method
  • Ejection type engine sand prevention system and method

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Embodiment Construction

[0032] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0033] For the structural shape of the helicopter, the integrated sand control system structure design is adopted, so that the shape of the sand control device is integrated with the shape of the helicopter, and the state of the air intake protection net is also taken into account, so that no excess flight resistance will be generated, and it is convenient for disassembly, maintenance and inspection. Among them, the sand control device is instal...

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Abstract

The invention belongs to the technical field of the air intake system of a helicopter engine, and discloses an ejection type engine sand prevention system and method. The system comprises a sand prevention device body, a sand prevention shutdown valve and an air guiding hose, wherein the sand prevention device body comprise a left sand prevention structure and a right sand prevention structure; the left sand prevention structure is installed on the left side of an airplane fairing; the right sand prevention structure is installed on the right side of the airplane fairing; the left sand prevention structure and the right sand prevention structure are embedded on the body of the airplane fairing and form an integral structure with the body of the airplane fairing; and the sand prevention shutdown valve is installed on a middle fixing plate platform on a helicopter engine fixing housing. Since the air guiding hose is connected with an engine P2 air guiding hole, the sand prevention shutdown valve and the sand prevention device body, the aerodynamic characteristics of the body of the helicopter are slightly affected, and the ejection type engine sand prevention system has a compact structure and is reliable in sealing.

Description

technical field [0001] The invention belongs to the technical field of helicopter engine air intake systems, and in particular relates to an ejector engine sand control system and method. Background technique [0002] When the helicopter is working close to the ground, the dust, sand, stones, weeds, ice and snow raised by the downwash airflow of the rotor are easily sucked into the engine with the airflow, causing serious wear and tear on the components in the engine intake passage, compressor blades, and even damage and bearing seizure Wait for failure. Therefore, for helicopters that often work in sand and dust environments, the installation of engine sand control devices is conducive to improving the safety and reliability of helicopter flight. Helicopter engines generally use vortex tube sand control devices for sand and dust protection. The sand-laden air flows through the vortex tube to generate high-speed rotation, and the heavy sand and dust are thrown out of the v...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/02
CPCB64D33/02B64D2033/022
Inventor 段勇亮林森什李洪江苏效平谢映涛袁野匡传树
Owner CHINA HELICOPTER RES & DEV INST
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