Method for optimizing overall performance of aero-engine

An aero-engine and optimization method technology, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as failure to take into account nacelle resistance, one-sided optimization results, and inability to fully consider coupling relationships, so as to shorten research and development. The period, the scheme design is reasonable, and the effect of reducing the convergence time

Active Publication Date: 2018-04-06
AECC COMML AIRCRAFT ENGINE CO LTD
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Problems solved by technology

[0002] The International Civil Aviation Organization has increasingly stringent requirements on aero-engine noise, pollution emissions and other indicators. Therefore, if the fuel consumption index is only considered in the initial stage of aero-engine conceptual design, the optimization result will be too one-sided, resulting in defects in aero-engine design.
With the continuous increase of the subjects involved, the optimization problem is also transformed into a multi-objective problem...

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  • Method for optimizing overall performance of aero-engine
  • Method for optimizing overall performance of aero-engine
  • Method for optimizing overall performance of aero-engine

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[0057] The present invention will be further described below in conjunction with specific embodiment and accompanying drawing, set forth more details in the following description so as to fully understand the present invention, but the present invention can obviously be implemented in many other ways different from this description, Those skilled in the art can make similar promotions and deductions based on actual application situations without violating the connotation of the present invention, so the content of this specific embodiment should not limit the protection scope of the present invention.

[0058] have to be aware of is, Figure 1 to Figure 3 All are for example only, and they are not drawn in accordance with the same scale conditions, and should not be taken as limitations on the protection scope of the actual claims of the present invention.

[0059] figure 1 It is a flow chart of the overall performance optimization method of the aero-engine, and the optimizat...

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Abstract

The invention aims to provide a method for optimizing overall performance of an aero-engine. The method comprises two rounds of optimization processes; and second optimization calculation comprises optimization of nacelle resistance, so that an aero-engine design scheme obtained by optimization is more comprehensive. An optimization platform takes an optimization result of first optimization calculation as an input of the second optimization calculation to reduce convergence time of the second optimization calculation. According to the method for optimizing the overall performance of the aero-engine, the optimization calculation speed can be increased; the research and development cycle can be shortened; and the optimization of the nacelle resistance is introduced in an engine concept design stage, so that the scheme is more reasonable in design.

Description

technical field [0001] The invention relates to the field of aero-engine design, and more particularly relates to a method for optimizing the overall performance of an aero-engine. Background technique [0002] The International Civil Aviation Organization has increasingly strict requirements on aero-engine noise, pollution emissions and other indicators. Therefore, if the fuel consumption index is only considered in the initial stage of aero-engine conceptual design, the optimization result will be too one-sided, resulting in defects in aero-engine design. With the increasing number of subjects involved, the optimization problem is also transformed into a multi-objective problem. The traditional manual iteration method is inefficient and cannot fully consider the coupling relationship between various subjects, so it is difficult to find the optimal solution to the multi-objective problem. [0003] The influence of nacelle resistance was not considered in the previous stage ...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/17G06F30/20
Inventor 罗钜郭福水邱超魏芳陈辉煌龙丹徐兴亚
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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