Modeling method of non-axisymmetrical hub for improving blockage at angular region

A non-axisymmetric, hub technology, used in non-variable volume pumps, components of pumping devices for elastic fluids, machines/engines, etc., can solve the problem of no structural modeling, no quantitative expression, pumping Questions about stomatal reliability, etc.

Active Publication Date: 2009-10-28
成都飞擎航空科技有限公司
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AI Technical Summary

Problems solved by technology

However, the industry has questioned the reliability of the suction hole during use of the suction gas
2. Convex and concave shape changes are produced on the hub. The purpose of the research is to control the speed of the leading and trailing edges of the blades to reduce losses. However, there is no quantitative expression for the convex and concave processing methods.
b. Control the inlet velocity of the pressure surface and the suction surface of the root blade to reduce the loss, but such studies have not given quantitative structural modeling

Method used

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  • Modeling method of non-axisymmetrical hub for improving blockage at angular region
  • Modeling method of non-axisymmetrical hub for improving blockage at angular region
  • Modeling method of non-axisymmetrical hub for improving blockage at angular region

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Embodiment Construction

[0026] The specific embodiment of the present invention is illustrated with examples. A fan rotor hub is redesigned according to the above-mentioned non-axisymmetric hub modeling method for improving corner blockage.

[0027] The design parameters of the fan rotor are shown in Table 1, and the blade surface parameters are known data.

[0028] Table 1 Design parameters of axial fan rotor

[0029]

[0030] 1. Determine the concave amplitude ΔR of the hub along the axial direction according to method (1):

[0031] 1) Take the calculation of the cross-sectional area of ​​the blade at z=0 as an example. It is known that the blade surface data is composed of 86 points on the pressure surface at the primitive level, 86 points on the suction surface, and 21 primitive levels in the radial direction. The two coordinates corresponding to z=0 of the pressure surface and the suction surface of each primitive level can be obtained by the method of difference, so 42 coordinate points c...

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Abstract

The invention relates to a modeling method of a non-axisymmetrical hub for improving blockage at angular regions of a fan / an air compressor. Re-modeling is conducted at a blade hub area, thus effectively relieving the blockage caused by angular region separation, and realizing the aim of the invention. Compared with the traditional modeling of the hub, the invention adopts the new modeling method of the non-axisymmetrical hub aiming at the blockage problem at the angular regions of the fan / the air compressor, thus effectively reducing the separation of the hub areas, enhancing the power-adding capability of the root part, and further improving the performance of the fan / the air compressor, and simultaneously expanding the stable working range of the fan / the air compressor.

Description

technical field [0001] The invention relates to a method for designing flow passages of an axial flow fan / compressor, in particular to a non-axisymmetric wheel hub modeling method for improving blockage in the corner area of ​​the fan / compressor. Background technique [0002] As the thrust-to-weight ratio of aero-engines continues to increase, increasing the stage load of the fan / compressor is an important means. However, the increase in load adds difficulty to the design of the fan / compressor. Under the strong adverse pressure gradient, the boundary layer will have serious separation in the hub corner area and cause blockage. Therefore, the research on the hub corner area has become one of the hot issues. [0003] Aiming at the separation problem of the hub corner area, domestic and foreign researches mainly focus on the following aspects: [0004] Two-dimensional and three-dimensional studies are carried out on the blade root region to solve the separation problem in th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/32
Inventor 李秋实侯安平杨春
Owner 成都飞擎航空科技有限公司
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