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Method and device for predicting aerodynamic performance of multi-stage axial flow compressor

A technology of axial flow compressor and aerodynamic performance, which is applied in the direction of axial flow pumps, machines/engines, mechanical equipment, etc., which can solve the problems of increased time consumption, affecting work efficiency, and low accuracy of estimated results, so as to improve accuracy , the effect of improving work efficiency

Active Publication Date: 2022-04-01
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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Problems solved by technology

To obtain a complete set of characteristic lines at different speeds, the time-consuming is multiplied
As a result, the estimated results cannot be obtained in time during the actual compressor development or engineering problem handling, which affects work efficiency
[0006] 2. The accuracy of the estimated results is low
In addition, the CFD simulation of the whole machine generally has the situation that the calculation error accumulates step by step, and the distribution relationship of the total pressure ratio of the compressor between the stages is quite different from the test. The more stages of the compressor, this phenomenon is about serious.
[0007] 3. Unable to accurately obtain the initial surge level
However, due to the large error in the distribution relationship of the total pressure ratio between the stages in the CFD simulation of the whole machine, it cannot truly reflect the actual working status and pressure ratio of each stage, and thus cannot accurately obtain the real first surge level.

Method used

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  • Method and device for predicting aerodynamic performance of multi-stage axial flow compressor
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  • Method and device for predicting aerodynamic performance of multi-stage axial flow compressor

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Embodiment Construction

[0033] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings that need to be used in the description of the embodiments. Obviously, the accompanying drawings in the following description are only some examples or embodiments of the present application, and those skilled in the art can also apply the present application to other similar scenarios. Unless otherwise apparent from context or otherwise indicated, like reference numerals in the figures represent like structures or operations.

[0034] As indicated in this application and claims, the terms "a", "an", "an" and / or "the" do not refer to the singular and may include the plural unless the context clearly indicates an exception. Generally speaking, the terms "comprising" and "comprising" only suggest the inclusion of clearly identified steps and elements, and these steps and elements do not constitute an exclusive list, and ...

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Abstract

The invention provides a method and device for estimating the aerodynamic performance of a multistage axial flow compressor. The method includes the following steps: pre-obtaining the first characteristic line family and the first complete machine characteristic line of each stage in the design state of the compressor, each first characteristic line family includes first characteristics at multiple conversion speeds line; obtain a predetermined level of characteristic line family in which the hardware in the compressor deviates from the design state, each characteristic line family includes a plurality of characteristic lines at converted speeds; obtain the second complete machine in which the hardware in the compressor deviates from the design state a characteristic line; and comparing the first overall machine characteristic line with the second overall machine characteristic line to obtain the influence of the deviation of the hardware state from the design state. The method and device of the invention have faster estimation efficiency and higher estimation accuracy.

Description

technical field [0001] The invention mainly relates to the design and test verification of an aero-engine or a gas turbine, in particular to a method and device for estimating the aerodynamic performance of a multi-stage axial flow compressor. Background technique [0002] The aerodynamic performance of an axial flow compressor is a set of extremely important parameters in the process of design, test verification, and service of an aero-engine or a gas turbine. This set of parameters can be used to evaluate the quality of the design of the compressor, monitor whether the working status of the compressor is normal, and analyze the faults that occur during the working process of the compressor, etc. [0003] In particular, during the development (design and test verification) of an aeroengine or gas turbine axial compressor, in many cases, it is necessary to predict and analyze the influence of certain influencing factors on the aerodynamic performance of the compressor. Thes...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D27/00F04D27/02F04D19/02G06F30/28G06F113/08G06F119/14G06F111/10
CPCF04D27/001F04D27/02F04D19/02G06F30/28G06F2113/08G06F2119/14G06F2111/10
Inventor 吴帆张晓诗翟志龙姜逸轩杨国伟曹传军李游
Owner AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD
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