Two-dimensional blade profile optimization design method and device based on self-adaptive grid

Abstract

The invention discloses a two-dimensional blade profile optimization design method and device based on a self-adaptive grid. The method for solving the two-dimensional blade profile flow field based on the adaptive grid comprises the following steps: drawing an initial grid for a two-dimensional blade profile, and performing viscosity calculation on the two-dimensional blade profile flow field toobtain flow field data corresponding to each node of the initial grid so as to form an initial flow field; and sniffing the initial flow field, marking grid nodes which do not accord with a thresholdcondition by utilizing a characteristic quantity detector, carrying out grid self-adaption until all the grid nodes meet the threshold condition, and finishing accurate calculation of the two-dimensional blade profile flow field to obtain an accurate response output value of a target function. A user does not need a high-precision solver, and the first-order precision to the second-order precisionprovided by common commercial computing software can meet requirements; at the position where the flow field change gradient is large, better robustness can be achieved through low-order solving; thegrid encryption position is determined through characteristic quantity detection, global encryption is avoided, the calculated amount is reduced, and the method has engineering practical use value.

Description

technical field [0001] The invention relates to the field of aerodynamic design of compressor blades, in particular to a two-dimensional blade shape optimization design method and device based on an adaptive grid. Background technique [0002] At present, the methods of producing compressor blades in the industry are as follows: figure 1 As shown, several two-dimensional airfoils are superimposed according to the accumulation line of a specific shape to generate a three-dimensional leaf. The aerodynamic level of the two-dimensional airfoil is directly related to the performance of the three-dimensional airfoil, which is very important in the design system. [0003] The relative Mach number of the entrance below the blade height of the transonic compressor is greater than 1 to achieve supersonic. The transonic stage has complex flow phenomena such as shock wave and its mutual interference with the boundary layer, and the leakage of the tip of the moving blade, which brings ...

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Problems solved by technology

With the improvement of calculation accuracy, the former has poor solution robustness and needs to customize a proprietary high-precision solver, which is not conducive to engineering implementation

[0006] Some studies have proposed three-dimensional aerodynamic design methods for ultra-high-load, ultra-low-speed, and large-bypass ratio fan rotors. For two-dimensional airfoils, standard airfoils or inverse problems or optimization methods are used for design, and the accuracy of flow field solutions is not mentioned. and accuracy-related issues

There are also some studies, as shown in Fig. 3(a) and Fig. 3(b), which adopt the RANS calculation method with second-order accuracy and above suitable for shock wave capture, and arrange more than 30 grid points within the shock wave wavelength, but It does not specifically point out the means of capturing the shock wave parameters, position and grid at the location of the encrypted shock wave

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