Method and system for calculating aerodynamic stability of turboshaft engine, equipment and medium

A turboshaft engine and stability technology, applied in complex mathematical operations, design optimization/simulation, instruments, etc., can solve problems such as the inability to calculate the influence of turboshaft engine intake pressure distortion on aerodynamic stability

Active Publication Date: 2021-09-07
AECC HUNAN AVIATION POWERPLANT RES INST
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Problems solved by technology

[0004] The present invention provides a method, system, equipment, and computer-readable storage medium for calculating the aerodynamic stability of a turboshaft engi...

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  • Method and system for calculating aerodynamic stability of turboshaft engine, equipment and medium
  • Method and system for calculating aerodynamic stability of turboshaft engine, equipment and medium
  • Method and system for calculating aerodynamic stability of turboshaft engine, equipment and medium

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Embodiment Construction

[0065] The embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.

[0066] Such as figure 1 As shown, the preferred embodiment of the present invention provides a method for calculating the aerodynamic stability of a turboshaft engine, which is used to assess the influence of intake pressure distortion on the aerodynamic stability of a turboshaft engine, comprising the following steps:

[0067] Step S1: Build a calculation model;

[0068] Step S2: Establish calculation areas and divide control volumes;

[0069] Step S3: Assuming that the aerodynamic parameters in each control volume are uniform in space, establish a set of governing equations to describe the flow inside the control volume:

[0070]

[0071] Among them, p represents the static pressure, T represents the static temperature, Indicates mass flow rate, L indic...

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Abstract

The invention discloses a method, system for calculating the aerodynamic stability of a turboshaft engine, equipment and a medium. The method comprises the steps: dividing a calculation model into a plurality of control bodies, and then calculating a control equation set for each control body to obtain the aerodynamic parameters of each control body; and combining an instability criterion to predict whether the pneumatic instability of the engine occurs under the given air inlet distortion condition, so that the influence of the air inlet pressure distortion on the pneumatic stability of the turboshaft engine can be accurately evaluated. A calculation model adopted by the method only focuses on parameters of inlet and outlet sections of the gas compressor, the whole combined gas compressor can be modularized, and static pressure, static temperature, mass flow and circumferential speed are adopted as variables to establish the equation set to describe flow in each control body. On one hand, all variables can be obtained through conversion of the equation set formula based on the four basic variables, on the other hand, the four basic variables can be conveniently obtained through a test means, and the data obtaining process is simplified.

Description

technical field [0001] The present invention relates to the technical field of evaluating the aerodynamic stability of a turboshaft engine, in particular, to a method, a system, a device, and a computer-readable storage medium for calculating the aerodynamic stability of a turboshaft engine. Background technique [0002] Helicopters have been widely used in military and civilian fields due to their advantages that fixed-wing aircraft do not have such as vertical take-off and landing and hovering. At the same time, they are less restricted by the site and are easy to use. The advantages of good performance, long range and easy maintenance have been the main power of helicopters since the 1960s. When the turboshaft engine is used in a helicopter, since the helicopter needs to meet different take-off and landing environments, such as sandy land, grassland, mountainous area, urban area, etc., and the flying altitude is not high, it is easy to absorb foreign objects, such as larg...

Claims

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Application Information

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IPC IPC(8): G06F30/28G06F30/20G06F17/12G06F119/14
CPCG06F30/28G06F30/20G06F17/12G06F2119/14Y02T90/00
Inventor 王召广杨宇飞王旭屠宝锋胡骏
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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