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Aerial turbofan engine low-pressure turbine rotor axial force real-time calculation method

A technology for aero-engines and low-pressure turbines, applied in design optimization/simulation, instruments, geometric CAD, etc., to achieve the effects of simplifying models, reducing calculation workload, and reducing calculation errors

Pending Publication Date: 2022-07-01
AECC SHENYANG ENGINE RES INST
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Problems solved by technology

[0004] The purpose of this application is to provide a real-time calculation method for the axial force of the low-pressure turbine rotor of an aeroengine, to solve or alleviate at least one of the problems in the background technology

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  • Aerial turbofan engine low-pressure turbine rotor axial force real-time calculation method
  • Aerial turbofan engine low-pressure turbine rotor axial force real-time calculation method
  • Aerial turbofan engine low-pressure turbine rotor axial force real-time calculation method

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Embodiment Construction

[0053] In order to make the implementation purpose, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.

[0054] like figure 1 As shown, the real-time calculation method for the axial force of the low-pressure turbine rotor of an aviation turbofan engine provided by the present application includes the following steps:

[0055] 1. Determine the main section parameters of the engine

[0056] The main cross-sectional parameters of the engine that can be measured in the engine test include: the total temperature of the fan inlet T 2 , Fan inlet total pressure P 2 , the total pressure P of the fan inlet 13 , compressor inlet total temperature T 25 , compressor inlet connotative total pressure P 23 , compressor outlet total temperature T 3 , compressor outlet t...

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Abstract

The invention provides a real-time calculation method for the axial force of a low-pressure turbine rotor of an aero-engine. The real-time calculation method comprises the steps that main section parameters of the aero-engine and related parameters which are highly related to the axial force of a flow channel of the low-pressure turbine rotor are determined; acquiring sample data of the main section parameters and the related parameters; fitting according to the sample data to obtain a runner axial force calculation model; the low-pressure turbine expansion ratio is corrected according to main runner performance parameter test data in an actual engine test; correcting the flow channel axial force calculation model obtained by fitting; determining an inner cavity axial force key parameter, an inner cavity axial force non-key parameter and a corresponding axial projection area coefficient when the engine is in a cold state; calculating the area variation of each inner cavity and the thermal state area deformation correction area coefficient of the inner cavity; and constructing an inner cavity axial force calculation model: combining the corrected runner axial force calculation model and the inner cavity axial force calculation model to obtain a low-pressure turbine rotor axial force calculation model.

Description

technical field [0001] The application belongs to the technical field of aero-engine design, and in particular relates to a real-time calculation method for the axial force of a low-pressure turbine rotor of an aviation turbofan engine. Background technique [0002] During the operation of the dual-rotor turbofan engine, the low-pressure turbine rotor component will bear a certain aerodynamic axial load, which directly affects the strength and life of the component, and also indirectly affects the reliability of the low-pressure rotor thrust bearing. In the whole machine test, the temperature of the component is high, the structural deformation is large, and the performance parameters of the inlet and outlet sections are difficult to measure, resulting in that the design value of the performance parameters of the component cannot be corrected, and the design error is large. [0003] The existing turbofan engine low-pressure turbine rotor axial force calculation method input ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/20G06F119/14
CPCG06F30/15G06F30/20G06F2119/14Y02T90/00
Inventor 许丽叶丛佩红宋洋张勇刘洋黄玉娟马志乐张志远于云飞
Owner AECC SHENYANG ENGINE RES INST
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