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Temperature distortion spectrum inverse design method based on discrete sequence

A discrete sequence and anti-design technology, applied in computer-aided design, design optimization/simulation, calculation, etc., to shorten the test cycle, avoid waste of manpower and material resources, and reduce test costs

Active Publication Date: 2019-08-02
XIAMEN UNIV
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to aim at the deficiencies of the existing accurate design method of temperature distortion map, calculate the heat source distribution according to the temperature distortion map, and provide a reverse design method of temperature distortion map based on discrete sequence

Method used

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  • Temperature distortion spectrum inverse design method based on discrete sequence
  • Temperature distortion spectrum inverse design method based on discrete sequence
  • Temperature distortion spectrum inverse design method based on discrete sequence

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Embodiment Construction

[0023] The following embodiments will further illustrate the present invention in conjunction with the accompanying drawings.

[0024] Embodiments of the present invention include the following steps:

[0025] 1) Determine the incoming flow velocity and the distance between the upstream distortion section and the downstream map section according to the given measurement section temperature map distribution;

[0026] 2) Generate the nozzle number M and nozzle distribution according to the temperature, number the arrangement and distribution of the nozzles sequentially, and set the heat flow combination sequence of each nozzle as a vector α;

[0027] 3) Divide the downstream target map section into units of magnitude N, and use the horizontal direction as the zero-angle line to sort the micro-units outward, and use interpolation based on the temperature distortion map The way to assign temperature to N units, and record it as the map column vector β;

[0028] 4) Construct the ...

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Abstract

The invention discloses a temperature distortion spectrum inverse design method based on a discrete sequence. The method comprises steps of determining the incoming flow speed and the distance betweenthe upstream distortion section and the downstream map section; numbering nozzle arranging distributing, and setting a heat flow combination sequence of each nozzle as a vector; dividing a downstreamtarget map cross section into units of magnitude N respectively, carrying out micro-unit sorting outwards on the divided micro-units by taking the horizontal direction as a zero angle line, and recording the micro-units as map column vectors beta; respectively constructing column vectors Q1,..., Qi,... and QM, and measuring a downstream temperature distortion spectrum; taking a generalized inverse matrix B for the matrix A, and determining the distribution of heat flow; according to the vector alpha, obtaining the state of each upstream nozzle. The specific temperature distortion spectrum isachieved by adjusting the heat flow injection intensity, the obtained result provides data support for exploring the temperature distortion under the real working condition, and therefore the inversedesign method is that a matrix A and the column vector beta are used for inversely solving the column vector alpha.

Description

technical field [0001] The invention relates to the aerodynamic stability evaluation technology of an aero-engine, in particular to a temperature distortion map inverse design method based on discrete sequences, which calculates the distribution of heat sources according to the temperature distortion map. Background technique [0002] The aerodynamic stability of an aeroengine is an important index for evaluating engine performance, which requires that the engine not only have superior performance in key design states, but also be able to resist the interference of destabilizing factors within the entire flight envelope and ensure sufficient available stability margins ( [1] Zhao Yunsheng. Research on Aerodynamic Stability Analysis System of Aeroengine [D]. Nanjing University of Aeronautics and Astronautics, 2013). However, during the process of aircraft formation flight and missile launch, the engine inlet will inevitably absorb heat flow, which will bring obvious temperatu...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F2119/08G06F30/20
Inventor 尤延铖李韧卓朱剑锋
Owner XIAMEN UNIV
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