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A Method of Suppressing Helicopter Propeller-Vortex Interference Noise

A vortex interference, helicopter technology, applied in the field of helicopter rotor blades, to achieve the effect of convenient maintenance, simple structure, and low manufacturing cost

Active Publication Date: 2020-04-24
XIAMEN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The object of the present invention is to provide a kind of method for suppressing helicopter propeller-vortex interference noise utilizing synthetic jet technology for the above-mentioned deficiency that existing suppressing helicopter rotor blade-vortex interference noise exists

Method used

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  • A Method of Suppressing Helicopter Propeller-Vortex Interference Noise

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Embodiment Construction

[0020] The concrete steps of the embodiment of the present invention are as follows:

[0021] Arrange at least one synthetic jet generator at a suitable position from the end surface of the blade tip, the synthetic jet generator is powered by a power supply, and generates a synthetic jet flow that is backward and downward relative to the forward direction of the rotor blade on the lower surface of the blade tip to weaken The strength of the blade tip vortex, and change its shedding direction, to avoid mutual interference between the blade tip vortex and subsequent blades, so as to achieve the effect of suppressing the noise of the blade-vortex interference.

[0022] The suitable position is 5-60mm.

[0023] The synthetic jet generator is provided with an inner cavity and a jet outlet with a caliber of 0.5-3mm in diameter, and the jet outlet is located on the lower surface of the blade tip and is flush with the lower surface. The synthetic jet generator can physically increase...

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Abstract

The invention provides a method for inhibiting blade-vortex interference noises of a helicopter and relates to helicopter rotor wing blades. At least one synthetic jet generator is distributed at a position, which has a proper distance to an end face, of a blade tip; the synthetic jet generator is powered by a power supply; synthetic jet, which is backward and downward relative to the frontward movement direction of the rotor wing blade, is generated on the lower surface of the blade tip and is used for weakening blade tip vortex strength, and a falling direction of the blade tip is changed; acondition that the blade tip vortex and subsequent blades have mutual interference is avoided so that the effect of inhibiting the blade-vortex interference noises is realized. Structure parameters of the synthetic jet generator can be optimized according to specific actual requirements, and the jet strength also can be changed through adjusting loading electrical parameters of the synthetic jetgenerator; blade-vortex interference is initiatively and flexibly intelligently controlled; the method has the advantages of simple structure, low manufacturing cost, convenience for maintenance, no changes of an original aerodynamic shape of the rotor wing blade tip and the like.

Description

technical field [0001] The invention relates to a helicopter rotor blade, in particular to a method for suppressing helicopter blade-vortex interference noise by using synthetic jet technology. Background technique [0002] Helicopters have unique properties such as vertical take-off and landing, hovering, and low-altitude and low-speed flight, making them more and more used in national defense and civilian fields. However, helicopters also have the disadvantage of excessive noise, which reduces their invisibility in the military, easily exposes their whereabouts prematurely, and greatly affects the battlefield penetration and survivability of helicopters; in terms of civilian use, excessive noise not only affects The ride comfort of the occupants also causes serious noise pollution, which does not meet the environmental protection requirements. [0003] Helicopter noise mainly comes from the aerodynamic noise of the rotor, which is generated by the unsteady motion and flow...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/46B64C27/467
CPCB64C27/46B64C27/467
Inventor 林麒陈约适刘汝兵
Owner XIAMEN UNIV