Test piece mechanism of high-pressure compressor

A compressor and test piece technology, applied in jet engine testing, gas turbine engine testing, etc., can solve the problem that the test results of components cannot fully reflect the working environment
CN112254973AActive Publication Date: 2021-01-22AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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Patent Information

Authority / Receiving Office
CN · China
Current Assignee / Owner
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD
Publication Date
2021-01-22

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Abstract

The invention provides a test piece mechanism of a high-pressure compressor. The mechanism is used for simulating the working environment of a whole turbofan engine and comprises a high-pressure compressor body, an inlet support plate and a transition section flow channel are arranged at the inlet of the high-pressure compressor body, a distortion device is arranged at the upstream of the inlet support plate and the transition section flow channel, and the distortion device is positioned in an outer flow channel of the inlet support plate and the transition section flow channel. The inventionprovides a high-pressure compressor test structure form capable of accurately simulating a complete machine environment. The high-pressure compressor test structure form comprises an inlet distortiondevice form, a high-pressure compressor body and an outlet simulation combustion chamber form. Meanwhile, a set of high-pressure compressor inlet distortion device structure scheme is provided, an inlet pressure profile can be generated, and the profile is consistent with the inlet pressure profile of the high-pressure compressor in the whole machine environment.
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Description

technical field

[0001] The invention relates to the field of a turbofan engine high-pressure compressor test piece, in particular to a high-pressure compressor test piece mechanism. Background technique

[0002] figure 1 It is a schematic diagram of the overall structure of a typical turbofan engine in the prior art.

[0003] Such as figure 1 As shown, in the prior art, a typical civil turbofan aeroengine is usually a double-duct configuration. During the whole machine test, after the air flows into the engine from the air inlet of the aircraft, it first enters the engine body through the fan 10, and then flows through the splitter ring and is divided into two parts, one part is discharged from the engine through the outer culvert, and the other part flows into the high pressure through the channel 20 of the transition section of the support plate. compressor. Wherein, the outlet position 30 of the support plate belongs to the interface of the high and low pressure air m...

Claims

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