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Aviation centrifugal pump blade profile optimization design method

An optimization design, centrifugal pump technology, applied in the direction of calculation, computational model, biological model, etc., can solve the problems of long iteration period, complex genetic algorithm coding, limited application of genetic algorithm, etc., to achieve the effect of improving optimization efficiency

Active Publication Date: 2019-07-12
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

However, the genetic algorithm has complex coding and long iteration period when solving, and the global search ability only depends on the mutation probability, which limits the application of genetic algorithm in centrifugal pump impeller optimization.

Method used

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  • Aviation centrifugal pump blade profile optimization design method
  • Aviation centrifugal pump blade profile optimization design method
  • Aviation centrifugal pump blade profile optimization design method

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Embodiment Construction

[0092] The technical solutions of the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0093] 1 Airfoil parametric design and numerical simulation

[0094] 1.1 Geometric model and profile parameterization process

[0095] The object of optimization design is the aviation fuel centrifugal pump with a specific speed of 63.13. Its main flow-passing components include inducer, centrifugal impeller and volute, and the design speed is 7600r / min. figure 1 The three-dimensional model and physical map of the fuel pump are shown.

[0096] The center plane of the centrifugal impeller blade can be regarded as the spatial expansion of the streamline on the axial plane. The research adopts the 5-point 4th Bezier curve to realize the parametric modeling of the blade shape by controlling the circumferential angle of the streamline of the hub and the rim. Such as figure 2 The shown abscissa θ is in radians...

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Abstract

The invention discloses an aviation centrifugal pump blade profile optimization design method. Under a Matlab platform, a five-point four-time bezier curve and a linear function are adopted to controlthe blade profile circumference angle distribution and the product superposition change rule, and internal flow field numerical simulation is carried out on 15 sets of design results through a software UG and Fluent combined batch processing method. On the basis of obtaining a calculation space boundary condition through curved surface interpolation, numerical solution is carried out on the dual-harmonic partial differential equation by adopting a central difference format, and a hypercurved surface performance agent model is sestaboished. Global optimization is carried out on the design variable based on an artificial fish swarm algorithm by taking the highest efficiency as an objective function. The result shows that the hypersurface agent model based on the double harmonic equation canensure that the test value and the predicted value are completely consistent, the wake effect in the optimized centrifugal impeller flow is obviously weakened, and the hydraulic efficiency is improved by 5.4% compared with that of a prototype pump.

Description

technical field [0001] The invention belongs to the technical field of aviation centrifugal pump design, and relates to a method for optimizing the blade profile of an aviation centrifugal pump. method. Background technique [0002] The fuel centrifugal pump is an important power component in the fuel system of an aeroengine. The optimized design of the impeller profile can improve the overall performance of the centrifugal pump without changing the main dimensions, which has very important engineering practical significance. A lot of research has been done on this. [0003] In the field of profile parameterization, Li Chun et al. used 3-degree B-spline curves to design the axial streamlines and streamline development lines of the front and rear cover plates of centrifugal pump impellers. Based on Bezier theory, Yin Mingxia, Liu Qunhui and others developed a two-dimensional airfoil parametric design software for turbomachines by using OpenGL as a development tool for graph...

Claims

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Application Information

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IPC IPC(8): G06F17/50G06N3/00
CPCG06N3/006G06F30/17G06F2111/06G06F30/20Y02T90/00
Inventor 刘显为肖红亮朱嘉兴李华聪符江锋
Owner NORTHWESTERN POLYTECHNICAL UNIV
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