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Bulky leading edge inlet guide vane

A guide and bulging technology, applied in the field of turbomachinery, can solve the problems of increasing the structural complexity of the inlet guide and increasing the weight of the compressor, so as to suppress large-scale separation, reduce the flow loss of the cascade, and prevent rotating stall or surge Effect

Active Publication Date: 2017-12-05
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

However, although the adjustable vanes can partially solve the above problems, this design increases the complexity of the inlet guide structure, introduces additional mechanisms, and increases the weight of the compressor

Method used

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  • Bulky leading edge inlet guide vane
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  • Bulky leading edge inlet guide vane

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Embodiment Construction

[0022] Embodiments of the present invention will be described in detail below, and the embodiments described below with reference to the accompanying drawings are exemplary, and are only used to explain the present invention, and cannot be construed as limiting the present invention.

[0023] Those skilled in the art can understand that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It should also be understood that terms such as those defined in commonly used dictionaries should be understood to have a meaning consistent with the meaning in the context of the prior art, and will not be interpreted in an idealized or overly formal sense unless defined as herein Explanation.

[0024] The purpose of the present invention is to use the principle of bionics to introduce the knob-like leading edge into the axial flow co...

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Abstract

The invention discloses a bulging leading edge inlet guide vane, which belongs to the technical field of impeller machinery. On the leading edge of the basic blade, there is a bulge formed by the bulge structure at different blade height sections. The line changes periodically, and the thickness of the bulge structure transitions smoothly along the leading edge. The invention improves the cascade flow field structure of the inlet guider of the compressor, and significantly reduces the flow loss of the cascade. The blades of the inlet guider at the bulging leading edge can not only improve the performance of the compressor within a certain range, but also prevent the guider from being caused by inlet swirl distortion. The large-scale separation of the blades improves the stability of the compressor and prevents the aero-engine from stalling or surging.

Description

technical field [0001] The invention discloses a bulging leading edge inlet guide vane, which belongs to the technical field of impeller machinery. Background technique [0002] The inlet guide is an important part of an aeroengine axial flow compressor, and its working performance has a great influence on the performance of the entire compressor. The total pressure loss of the inlet guide increases with the increase of the airflow angle of attack, and when the angle of attack reaches a certain value, the increasing trend of the total pressure loss is significantly intensified. This angle of attack is defined as the critical angle of attack. However, the angle of attack of the inlet guide cannot always be below the critical angle of attack. When the angle of attack of the airflow is greater than the critical angle of attack and continues to increase, the range of the separation zone of the suction surface of the inlet guide gradually increases, even covering The entire suc...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/38F04D29/66
Inventor 屠宝锋张凯刘华胡骏阮立群
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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