Low-pressure turbine shaft space layout design method

A low-pressure turbine shaft and layout design technology, applied in design optimization/simulation, geometric CAD, sustainable transportation, etc., can solve the problems of long design cycle and low design efficiency of low-pressure turbine shaft, achieve short calculation cycle, solve low-pressure shaft The effect of dynamic characteristic estimation and high design efficiency

Pending Publication Date: 2022-05-24
AECC SHENYANG ENGINE RES INST
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Problems solved by technology

[0009] The purpose of this application is to provide a low-pressure turbine shaft spatial layout design method to solve the problems of low design efficiency and long design cycle of low-pressure turbine shafts in the prior art

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[0019] 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.

[0020] A low-pressure turbine shaft spatial layout design method, compared with the preliminarily selected inner and outer diameters of the low-pressure shaft in the prior art, the accuracy of the inner and outer diameters cannot be judged, so repeated trial and error is required, and the efficiency is low; the present application The standard low-pressure shaft size is given first, and then the numerical range of other sizes is deduced in reverse. Through such a reverse deduction method, data can be quickly selected, thereby ensuring the efficiency of the design.

[0021] like figure 1 shown, the specific design includes:

[0022] Step S100, determine the ...

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Abstract

The invention belongs to the field of aero-engine overall structure design, and relates to a low-pressure turbine shaft space layout design method, which comprises the following steps: firstly, giving an overall performance input parameter and a temperature boundary parameter of a low-pressure shaft to determine an overall structure cavity space layout scheme, a preliminary layout of the low-pressure shaft, the size of the low-pressure shaft and a material range; determining the basic physical properties of the low-pressure shaft by selecting the material of the low-pressure shaft; initial values of the inner diameter size and the shaft length of the low-pressure shaft and initial static strength design parameters are given firstly, and then key control sizes of other low-pressure shaft schemes are obtained according to program iterative calculation. Due to the adoption of program automatic iterative computation, the scheme design is quick and convenient. In the subsequent static strength analysis, machinability analysis and bearing DN value analysis, due to the fact that variables are reduced, numerical values needing to be improved can be rapidly determined, and therefore the final design of the low-pressure turbine shaft scheme is rapidly completed. The method is convenient to use, high in design efficiency, short in calculation period and low in working cost.

Description

technical field [0001] The present application belongs to the field of aero-engine overall structure design, and in particular relates to a low-pressure turbine shaft space layout design method. Background technique [0002] The overall structural layout design of aero-engine refers to the proposal of the overall structural layout scheme that meets the requirements of product functions and performance indicators according to the use requirements, environmental conditions and functional requirements of the engine. In the process of aero-engine scheme design, the spatial layout of the low-pressure turbine shaft is an important part of the overall scheme layout. [0003] The existing design method for the spatial layout of the low-pressure turbine shaft of a twin-rotor turbine engine includes nine design steps: [0004] 1. Determine the overall performance input parameters, 2. Determine the temperature boundary, 3. Determine the material selection parameters, 4. Determine the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/20
CPCG06F30/17G06F30/20Y02T90/00
Inventor 刘旭阳徐雪韩佳杨天宇郭帅帆
Owner AECC SHENYANG ENGINE RES INST
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