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Combined surge eliminating method and multistage axial flow compressor experiment platform

An experimental platform and compressor technology, applied in mechanical equipment, machine/engine, pump control, etc., can solve difficult problems such as one-time and effective asthma relief, and achieve the effect of ensuring timeliness and effectiveness and improving work safety

Active Publication Date: 2020-11-13
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In view of this, the embodiment of the present disclosure provides a combined anti-asthma method and a multi-stage axial flow compressor experimental platform, which can solve the technical problem that it is difficult to effectively relieve the anti-asthma at one time when the surge intensity is high, and can target the Low-speed surge and high-speed surge, through different anti-surge methods, ensure the timeliness and effectiveness of anti-surge, and effectively improve the working safety of the compressor

Method used

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  • Combined surge eliminating method and multistage axial flow compressor experiment platform
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  • Combined surge eliminating method and multistage axial flow compressor experiment platform

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Embodiment Construction

[0063]Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. The description of the exemplary embodiments is illustrative only, and in no way restricts the disclosure, its application or uses. The present disclosure can be implemented in many different forms and is not limited to the embodiments described here. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that relative arrangements of parts and steps, compositions of materials, numerical expressions and numerical values ​​set forth in these embodiments should be interpreted as illustrative only and not as limiting, unless specifically stated otherwise.

[0064] "First", "second" and similar words used in the present disclosure do not indicate any order, quantity or importance, but are only used to disting...

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Abstract

The invention relates to a combined surge eliminating method. The method comprises the steps that a first combined surge eliminating scheme and a second combined surge eliminating scheme are set according to the working condition of a gas compressor; when the rotating speed of the gas compressor is lower than the set rotating speed, the first combined surge eliminating scheme is executed until surge is eliminated; when the rotating speed of the air compressor is higher than the set rotating speed, the first combined surge eliminating scheme is executed firstly, the first combined surge eliminating scheme is stopped when surge is eliminated, and the second combined surge eliminating scheme is executed until surge is eliminated while the first combined surge eliminating scheme is kept to beexecuted when surge is not eliminated; and the first combined surge eliminating scheme comprises opening an exhaust throttle valve and an inter-stage air entraining control valve, and the second combined surge eliminating scheme comprises reducing the rotating speed of the air compressor and adjusting the angle of an adjustable blade. The technical problem that when the surge strength is large, surge is difficult to effectively eliminate at a time can be solved, the timeliness and effectiveness of surge eliminating can be ensured through different surge eliminating modes aiming at low-rotating-speed surge and high-rotating-speed surge in the air compressor, and the working safety of the air compressor is effectively improved.

Description

technical field [0001] The present disclosure relates to the field of aero-engine experiments, in particular to a combined anti-breathing method and a multi-stage axial flow compressor experimental platform. Background technique [0002] When the air flow through the compressor is reduced to a certain extent, so that the operating point enters the left side of the surge boundary line, then the entire compressor cannot work stably, and the air flow will suddenly increase Suddenly small, the pressure will be high and low, and even the airflow from the compressor to the outside atmosphere will flow backwards, and at the same time, there will be a huge sound, which will cause the unit to vibrate strongly. This phenomenon is called surge. [0003] On the one hand, surge will lead to a decline in the overall performance of the engine, specifically manifested as a decrease in engine power, a decrease in thrust, an increase in fuel consumption, and an increase in exhaust temperature...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D27/02F04D27/00
CPCF04D27/001F04D27/0246F04D27/0253F04D27/0261F04D27/0284
Inventor 孙震宇金宗亮甘露
Owner AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD
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