Gas compressor three-dimensional numerical simulation method and device
A technology of three-dimensional numerical and simulation methods, which is applied in CAD numerical modeling, complex mathematical operations, electrical digital data processing, etc., can solve the problems that the calculation accuracy is difficult to meet the level of engine development and cannot describe the three-dimensional flow characteristics of compressor blades. To achieve the effect of alleviating the long calculation time
Pending Publication Date: 2022-08-09
BEIHANG UNIV
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Problems solved by technology
However, due to the use of dimension reduction processing, it is impossible to describe the three-dimensional flow characteristics of the complex distorted flow field in the compressor blade row, and the calculation accuracy cannot meet the requirements of the current engine development level.
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[0032] In order to make the objectives, technical solutions and advantages of the present application more clear, the present application will be described in further detail below in conjunction with the specific embodiments and with reference to the accompanying drawings. It should be understood that these descriptions are exemplary only and are not intended to limit the scope of the application. Also, in the following description, descriptions of well-known structures and techniques are omitted to avoid unnecessarily obscuring the concepts of the present application.
[0033] In the description of the present application, it should be noted that the terms "first", "second" and "third" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance.
[0034] figure 1 It is a schematic flowchart of a three-dimensional numerical simulation method for a compressor according to an embodiment of the present application.
[0035] lik...
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The invention discloses a three-dimensional numerical simulation method and device for a gas compressor, and the method comprises the steps: calculating a first flow field of the gas compressor through a steady Reynolds average method under a uniform gas inlet condition; control volume analysis is conducted on the first flow field, a three-dimensional volume force initial item is obtained, and the three-dimensional volume force initial item is force borne by the compressor blade; the flow coefficient and the load coefficient of the gas compressor are compared, the correlation between the local relative airflow angle and the relative load coefficient is established, and the local relative airflow angle represents the local air inlet attack angle; establishing a correlation between a local relative airflow angle and a relative loss coefficient according to the initial item of the three-dimensional volume force in combination with the constraint of an incompressible condition; and calculating a three-dimensional volume force source item according to the relative load coefficient and the relative loss coefficient. According to the technical scheme, the technical problem that a traditional URANS method is long in calculation time is solved, and the technical problem that a compressor simplified model cannot truly reflect the three-dimensional flow characteristics of a complex distortion flow field is also solved.
Description
technical field [0001] The present application relates to the technical field of compressor fluid mechanics, and in particular, to a method and device for three-dimensional numerical simulation of a compressor. Background technique [0002] In the actual working process of the aero-engine, the inhalation of the boundary layer and the maneuvering flight at a high angle of attack will make the distribution of the aerodynamic parameters of the compressor inlet uneven. Flow field distortion has various effects on the compressor: intake distortion has a certain impact on the performance of the compressor, that is, the pressure ratio and efficiency of the compressor are reduced relative to the uniform intake conditions; but more importantly, the intake air Distortion has a significant impact on the aerodynamic stability of the compressor and the compression system in which it resides, causing it to stall prematurely, leading to propulsion system compatibility issues. This compati...
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IPC IPC(8): G06F30/20G06F30/15G06F17/11G06F119/14G06F111/10
CPCG06F30/20G06F30/15G06F17/11G06F2119/14G06F2111/10Y02T90/00
Inventor 潘天宇李秋实凌健蓝刘仕杰郑孟宗
Owner BEIHANG UNIV