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A two-stage axial flow compressor

A technology for axial flow compressors and compressors, applied in axial flow pumps, mechanical equipment, engine manufacturing, etc., can solve the problems of inconvenient compressor performance requirements, and achieve the effect of increasing the flexible polishing process and increasing the intake flow

Active Publication Date: 2022-02-22
上海尚实航空发动机股份有限公司
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0003] The requirements for the axial dimension of the engine to be shortened by the existing installation target make it inconvenient for the overall length of the engine to meet the specified performance requirements of the compressor; and it is inconvenient to adjust the size of the air flow and protect the air flow channel from closing when it is not in use

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  • A two-stage axial flow compressor
  • A two-stage axial flow compressor
  • A two-stage axial flow compressor

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Embodiment Construction

[0027] The following will be combined with Figure 1-7 The present invention is described in detail, and the technical solutions in the embodiments of the present invention are clearly and completely described. Apparently, 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.

[0028] see figure 1 , figure 2 , image 3 and Figure 4 , a two-stage axial flow compressor of the present invention, comprising a secondary compressor rectifying ring 1, a secondary axial compressor impeller 2, a primary compressor rectifying ring 3, a primary axial compressor impeller 4, bearing positions Air seal 5, centrifugal compressor impeller 6, intermediate locking shaft 7, centrifugal compressor outer casing 8, air intake hole 9, comp...

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Abstract

The invention discloses a two-stage axial flow compressor, which comprises a rectification ring of the second stage compressor, an impeller of the second stage axial flow compressor and a rectification ring of the first stage compressor. The invention adjusts the vane angles of the impellers of the two axial flow compressors , increase the diameter of the impeller, increase the throat area between the blades and increase the annular area of ​​the flow channel to increase the intake flow; add flexible polishing process to the intake channel to improve the surface roughness of the intake channel to reduce the intake resistance At the same time, the surface structure of the blade is improved to increase the fatigue resistance of the blade; the impeller material is replaced by TC11 forgings with higher strength, and the overall machining is completed. Smoothness; through the cooperation of the gear and the arc-shaped rack, the circular baffle is moved to the circular air port to adjust the size of the internal air intake channel, which can be adjusted according to the size of the air flow and the air flow channel can be closed when not in use protection.

Description

technical field [0001] The invention relates to the related field of a turboprop engine, in particular to a two-stage axial flow compressor. Background technique [0002] The function of the compressor is mainly to compress, rectify, and divert the external air step by step, and finally enter the combustion chamber casing, and mix it with the fuel atomized by the fuel nozzle to form an oil-gas mixture, which is ignited by the ignition nozzle and then burned to perform work; With the continuous development of science and technology and the continuous maturity of domestic aviation technology, the general aviation market has an increasing demand for civil aviation engines. Engines require high performance indicators, compact structure, easy installation, and easy maintenance. [0003] The requirements for the axial dimension of the engine to be shortened by the existing installation target make it inconvenient for the overall length of the engine to meet the specified performan...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D19/02F04D29/32F04D29/52F04D27/00F04D29/36F04D29/38F04D29/02F04D29/28
CPCF04D19/022F04D19/046F04D29/321F04D29/522F04D27/002F04D29/323F04D29/324F04D29/023F04D29/284F05D2250/621
Inventor 张礼强陈波高华黄啸王石柱
Owner 上海尚实航空发动机股份有限公司
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