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Thickening and Arrangement Method of Compressor and Its Blade System

A technology of blade system and arrangement method, which is applied in the field of fluid turbomachinery, and can solve problems such as uneven distribution of blades, difficulty in ensuring the performance of the compressor at low speed, and influence on the performance of the compressor

Active Publication Date: 2016-06-29
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] Generally speaking, the compressors with thickened partial blades in the prior art have at least the following disadvantages: 1) In the multi-stage environment of the compressor, due to the thickening of some blades, the total channel area of ​​the compressor before and after the thickening changes, Therefore, it is difficult to ensure that the low-speed performance of the entire compressor is not affected; 2) Due to the thickening of some blades, the distribution of the blades in the circumferential direction is uneven, resulting in the performance of the compressor being affected

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  • Thickening and Arrangement Method of Compressor and Its Blade System
  • Thickening and Arrangement Method of Compressor and Its Blade System
  • Thickening and Arrangement Method of Compressor and Its Blade System

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Embodiment Construction

[0033] As required, specific embodiments of the invention will be disclosed herein. However, it should be understood that the embodiments disclosed herein are merely typical examples of the invention, which can be embodied in various forms. Therefore, specific details disclosed herein are not to be considered limiting, but merely as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the invention in any appropriate way in practice, This includes taking various features disclosed herein and combining features that may not be expressly disclosed herein.

[0034] First, the compressor according to a preferred embodiment of the present invention includes a plurality of stator blades 1 arranged in the circumferential direction, and image 3 Only the structure of some stator blades of the compressor is shown. like image 3 As shown, there is an airflow channel 2 between every two adjacent stator blades 1 . In this compres...

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Abstract

The invention relates to a compressor, which belongs to the field of fluid impeller machinery. The compressor includes a plurality of stator blades arranged in the circumferential direction, and there is an air flow channel between every two adjacent stator blades, wherein the plurality of stator blades arranged in the circumferential direction are formed by periodically staggered thick stator blades blade and a thin stator blade, the leading edge of the thick stator blade is aligned with the leading edge of the thin stator blade, and the blade back angle of attack of the thick stator blade is equal to the blade back angle of attack of the thin stator blade, so that The front edge flow of the thick stator vane and the thin stator vane is guaranteed to have good consistency, and the throat area of ​​each airflow channel is basically the same, which ensures that the flow rate of each airflow channel is equal, and reduces the inhomogeneity of the outlet. The invention also relates to a method for thickening and arranging the blade system of a compressor.

Description

technical field [0001] The present invention generally relates to fluid turbomachinery, and more particularly relates to a compressor and a method for thickening and arranging the blade system of the compressor. Background technique [0002] The compressor is one of the core components of an aero-engine, and its function is to compress air to increase the total temperature and pressure of the gas. The flow part of the compressor is composed of rotor blades and stator blades arranged alternately. The rotor blades perform work on the air flow, converting mechanical work into kinetic energy and static pressure energy of the gas, while the stator blades convert the kinetic energy of the gas into static pressure rise, and Change the direction of air flow to meet the needs of the next stage rotor blades. The rotor blades and the stator blades are evenly arranged along the circumferential direction. figure 1 It is a structural schematic diagram of some stator blades of an existin...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/26
Inventor 杨平冯锦璋谢伟亮许峰
Owner AECC COMML AIRCRAFT ENGINE CO LTD