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Centrifugal compressor and design method thereof

A technology of centrifugal compressor and design method, which is applied in computer-aided design, mechanical equipment, calculation, etc., can solve the problem that the total pressure ratio cannot be further improved, and achieve the goal of improving unfavorable air intake conditions, increasing pressure, and increasing working capacity Effect

Active Publication Date: 2019-03-26
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Abstract
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Problems solved by technology

[0003] The invention provides a centrifugal compressor and its design method to solve the problem that the existing centrifugal compressor cannot further increase the total pressure ratio

Method used

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  • Centrifugal compressor and design method thereof
  • Centrifugal compressor and design method thereof
  • Centrifugal compressor and design method thereof

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Embodiment Construction

[0034] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0035] figure 1 is one of the schematic diagrams of the centrifugal compressor in the preferred embodiment of the present invention; figure 2 It is the second schematic diagram of the centrifugal compressor of the preferred embodiment of the present invention; image 3 It is the third schematic diagram of the centrifugal compressor in the preferred embodiment of the present invention; Figure 4 is the fourth schematic diagram of the centrifugal compressor in the preferred embodiment of the present invention; Figure 5 is a schematic diagram of a forward-swept structure of a preferred embodiment of the present invention; Image 6 It is a schematic diagram of the outlet velocity triangle of ...

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Abstract

The invention provides a centrifugal compressor and a design method thereof. The centrifugal compressor comprises front-row centrifugal vane wheels, rear-row centrifugal vane wheels, and axial diffusers, wherein the front-row centrifugal vane wheels are used for forming an air flow channel, so that an air flow can pass through the air flow channel and is acted by utilizing a centrifugal force; therear-row centrifugal vane wheels are located at air flow outlets of the front-row centrifugal vane wheels and are used for forming an air flow channel, so that an air flow can pass through the air flow channel and is acted by utilizing a centrifugal force; the axial diffusers are located at air flow outlets of the rear-row centrifugal vane wheels and are used for retarding and diffusing an air flow, so that the air flow is turned into the axial direction from the radial direction; the rotation directions of the rear-row centrifugal vane wheels are opposite to the rotation directions of the front-row centrifugal vane wheels, so that the front-row centrifugal vane wheels provide reverse prerotation for the rear-row centrifugal vane wheels; and air flow inlet parts of blades of the rear-rowcentrifugal vane wheels are of swept forward structures. The centrifugal compressor provided by the invention adopts the rear-row centrifugal vane wheels to replace conventional radial diffusers and fully utilizes the double advantages of high centrifugal force and reverse prerotation power capability so as to achieve the aim of greatly improving the overall pressure ratio of the centrifugal compressor under the condition with a compact structure.

Description

technical field [0001] The invention relates to the technical field of centrifugal compressors, in particular, to a centrifugal compressor. In addition, the invention also relates to a design method of a centrifugal compressor. Background technique [0002] In order to further increase the total pressure ratio of existing centrifugal compressors, on the one hand, the tangential velocity at the outlet of the centrifugal impeller can be increased, but limited by the material, the tangential velocity cannot be increased indefinitely, and the potential for increasing the total pressure ratio is limited. The structural strength and life of the centrifugal compressor are unfavorable. On the other hand, a multi-stage centrifugal compressor can be used, but the stroke of the gas compression channel is longer and there are large curvature turns between the channels, resulting in serious flow loss, which is not conducive to the improvement of the efficiency of the centrifugal compres...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D17/12F04D29/28G06F17/50
CPCF04D17/12F04D29/286G06F30/17G06F2111/10G06F2119/06
Inventor 谢建陈璇金海良邹学奇银越千温泉
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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