Multi-time-step unsteady icing calculation method and system and storage medium

A calculation method and multi-time technology, applied in design optimization/simulation, wind power generation, wind turbines, etc., can solve problems such as slow calculation speed, low calculation accuracy, and inability to describe liquid film flow, etc., to achieve high accuracy and improve simulation The effect of high precision and fast calculation speed

Active Publication Date: 2020-07-10
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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Problems solved by technology

[0005] The purpose of the present invention is to provide a multi-time-step unsteady icing calculation method, system and storage medium, aiming to solve the problem of lo

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  • Multi-time-step unsteady icing calculation method and system and storage medium

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[0038] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0039] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0040] figure 1It is a flow chart of the multi-time-step unsteady icing calculation method suitable for wind turbines described in the present invention. The present invention provides a multi-time-step unsteady icing calculation method suitable for wind turbines, comprising the following steps:

[...

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Abstract

The invention provides a multi-time-step unsteady icing calculation method and system and a storage medium. The method comprises the steps that S1, flow field and cloud and mist field information is read in; S2, the relative inflow wind speed and the relative inflow angle of attack alpha re1 of blades extending to different section positions are calculated; S3, a two-dimensional wing-shaped localliquid water collection coefficient is calculated; S4, liquid film icing phase change is calculated; S5, according to the icing configuration, through grid deformation calculation, a numerical calculation grid is updated, and icing calculation of the next time step is started, wherein the wind wheel plane induction speed updating time step is delta T1, the local wing-shaped icing flow field updating time step is delta T2, the local icing wing-shaped collection coefficient updating time step is delta T3, and delta T1>delta T2> delta T3. According to the method, different icing calculation updating step lengths are formulated in the step S5 for different icing time scales, the icing calculation efficiency of a wind turbine can be improved to the maximum extent, and therefore ultra-long icingcalculation of a large wind turbine becomes possible.

Description

technical field [0001] The invention belongs to the technical field of wind turbine engineering, and in particular relates to a multi-time-step unsteady icing calculation method, system and storage medium. Background technique [0002] Wind turbine icing is a complex physical process. The icing of wind turbines can be mainly divided into sedimentary icing and cloud icing, and mainly cloud icing. When the ambient temperature, liquid water content (Liquid Water Content, LWC) and relative inflow wind speed are low, the supercooled water droplets in the air will freeze immediately after hitting the blade surface, forming frost ice with a more regular shape; when the LWC, relative inflow When the wind speed is high and the ambient temperature is close to 0 °C, the supercooled water droplets will form a liquid film on the blade surface after hitting the blade surface. The liquid film transports the collected liquid water under complex forces such as wind shear force, environment...

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Application Information

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IPC IPC(8): F03D80/40G06F30/28
CPCF03D80/40Y02E10/72
Inventor 王强易贤刘宇任靖豪李维浩
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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