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Two-stage axial flow gas compressor

An axial flow compressor and compressor technology, applied in axial flow pumps, mechanical equipment, engine manufacturing, etc., can solve problems such as inconvenient compressor performance requirements

Active Publication Date: 2021-07-06
上海尚实航空发动机股份有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

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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  • Two-stage axial flow gas compressor
  • Two-stage axial flow gas compressor
  • Two-stage axial flow gas compressor

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Embodiment Construction

[0028] 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.

[0029] see figure 1 , figure 2 , image 3 with 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, com...

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Abstract

The invention discloses a two-stage axial flow gas compressor which comprises a second-stage gas compressor rectifying ring, a second-stage axial flow gas compressor impeller and a first-stage gas compressor rectifying ring. The blade profile angles of the two axial flow gas compressor impellers are adjusted, the diameters of the impellers are increased, the throat area between blades is increased, and the annular area of a flow channel is increased, so that the gas inlet flow is increased. A flexible polishing process is added to the gas inlet flow channel to reduce the surface roughness of the gas inlet flow channel, so that gas inlet resistance is reduced. Meanwhile, the surface organization structure of the blades is improved so as to increase the fatigue resistance of the blades. The materials of the impellers are replaced by TC11 forge pieces with higher strength to be integrally machined and manufactured, and the machined impellers are subjected to flexible polishing so as to enhance the surface strength of the blades and improve the surface smoothness of the blades. Through cooperation of a gear and an arc-shaped rack, a circular blocking piece moves to a circular air opening to adjust the size of the internal gas inlet channel, adjustment can be conducted according to the gas flow, and the gas flow channel is closed for protection when not used.

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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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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