Compressor and thickening and arranging method of blade system of compressor
A technology of blade system and arrangement method, which is applied in the field of fluid turbomachinery, and can solve problems such as difficulty in ensuring low-speed performance of the compressor, influence of compressor performance, and uneven distribution of blades
Active Publication Date: 2014-03-12
AECC COMML AIRCRAFT ENGINE CO LTD
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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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[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. Such as image 3 As shown, there is an airflow channel 2 between every two adjacent stator blades 1 . In this comp...
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The invention relates to a compressor, and belongs to the field of fluid impeller machines. The compressor comprises a plurality of circumferentially-arranged stator blades, an air flow channel is formed between every two adjacent stator blades, the circumferentially-arranged stator blades are composed of the thick stator blades and the thin stator blades, the thick stator blades and the thin stator blades are periodically arranged in a stagger mode, the front edges of the thick stator blades are aligned with the front edges of the thin stator blades, the blade back attack angles of the thick stator blades are equal to the blade back attack angles of the thin stator blades, it is guaranteed that front edge flowing of the thick stator blades and the thin stator blades has the good coincidence, the throat areas of the air flow channels are basically coincident, it is guaranteed that flow of the air flow channels is equal, and the non-uniformity of an outlet is reduced. The invention further relates to a thickening and arranging method of a blade system of the 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...
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IPC IPC(8): F04D29/26
Inventor 杨平冯锦璋谢伟亮许峰
Owner AECC COMML AIRCRAFT ENGINE CO LTD