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1.5-level transonic axial-flow air compressor testing apparatus

A technology of axial flow compressor and test device, which is applied in the field of test machines, to achieve the effects of increased manufacturing difficulty, improved sensitivity, and compact structure

Inactive Publication Date: 2014-08-06
HANGZHOU TURBINE POWER GRP +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, in order to digest and absorb the imported F-class gas turbines in China, it is necessary to provide detailed data of the flow field of the transonic compressor through experiments, and there is no test bench in this regard in China before

Method used

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  • 1.5-level transonic axial-flow air compressor testing apparatus
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  • 1.5-level transonic axial-flow air compressor testing apparatus

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Embodiment 1

[0034] This embodiment describes as Figure 1-8 As shown, the 1.5-stage transonic axial flow compressor test device provided in this embodiment mainly includes a compressor 1, a high-speed diaphragm coupling 2, a gearbox 3, a low-speed end coupling 4, a motor 5, and a common chassis 6 , the motor 5 drives the gearbox 3 to rotate through the low-speed coupling 4; after the gearbox 3 speeds up, it drives the compressor 1 through the high-speed diaphragm coupling 2.

[0035] Among them, the compressor 1 is the most complex and core component. The compressor 1 mainly includes a flow part, an air inlet 7, an air outlet 13, a rotor 18, a lubrication system 14, a bearing system 15, a sealing system 17 and a measurement system 8. When the engine 1 is working, the air enters the flow part from the air inlet 7, and then is discharged into the atmosphere through the air outlet 13; the rotor 18 is supported by the bearing system 15 and lubricated and cooled by the lubrication system 14; i...

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Abstract

The invention discloses a 1.5-level transonic axial-flow air compressor testing apparatus which comprises an air compressor, a high-speed membranous disc coupling, a gear box, a low-speed-end coupling, a motor and a common base plate. The motor is in transmission connection with the gear box by the low-speed-end coupling, the gear box is further in transmission connection with the air compressor by the high-speed membranous disc coupling, the air compressor is sequentially provided with an air inlet channel, a rotor, a through-flow portion and an air outlet channel along a flow direction of air, an openable circular hole is formed in the air outlet channel, and the rotor is provided with a lubricating system and is supported by a bearing system. The 1.5-level transonic axial-flow air compressor testing apparatus has the advantages that when the air compressor works, the air flows into the through-flow portion from the air inlet channel and is exhausted into the atmosphere via the air outlet channel; the high-speed membranous disc coupling is excellent in compensation ability, so that shafting requirements can be met; the rotor is supported by the bearing system and is lubricated and cooled by the lubricating system; a measuring system is reasonably arranged, so that test prototype parameters in transonic flow procedures can be acquired.

Description

technical field [0001] The invention relates to a testing machine for a high-speed transonic axial-flow compressor, in particular to a test device for a 1.5-stage transonic axial-flow compressor. Background technique [0002] The compressor is one of the important components of the gas turbine, which has an important influence on the performance of the gas turbine. The transonic stage design of the compressor is mainly used in the first stage of a civil aviation engine or in the first few stages of a military engine. The stagnation pressure ratio of the transonic stage of the compressor is generally around 1.2-2.2, among which the civilian use is close to 1.2, and the military use is close to 2.2. The design level of the transonic stage of the compressor greatly affects the performance of the compressor, so the study of the transonic stage of the compressor is very necessary for designing a new generation of compressors or improving the existing compressors. [0003] Nowad...

Claims

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Application Information

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IPC IPC(8): G01M15/14
Inventor 徐志明顾春伟周一飞叶钟黄庆春
Owner HANGZHOU TURBINE POWER GRP
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