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Compressor rotor blade meeting both pneumatic and strength requirements

A compressor rotor and blade technology, which is applied in the field of aerodynamic design of turbomachinery, can solve the problems of blade aerodynamic performance and strength at the same time, and achieve the effect of expanding the stable working range, good practical application value, and continuous curvature

Inactive Publication Date: 2017-01-25
友铂空天动力(深圳)有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to overcome the problem that the aerodynamic performance and strength of blades are difficult to be considered simultaneously in the existing related technologies, the present invention provides a compressor rotor blade structure that takes into account both aerodynamics and strength.

Method used

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  • Compressor rotor blade meeting both pneumatic and strength requirements
  • Compressor rotor blade meeting both pneumatic and strength requirements
  • Compressor rotor blade meeting both pneumatic and strength requirements

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Embodiment Construction

[0018] The invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0019] see figure 1 , the present invention provides a compressor rotor blade structure that takes into account both aerodynamics and strength. Half leaf 11, middle portion 12, and upper half leaf 13; the inner curved surface 1a is concave, and its concave degree gradually decreases from bottom to top; the outer curved surface 1b is convex, and its convex degree is from It gradually decreases from bottom to top; the curvature of the cross section of the middle part 12 is zero.

[0020] In the present invention, the inner curved surface 1a faces the air outlet, and the outer curved surface 1b is located on the side of the air inlet, and the height h of the lower half blade 11 accounts for 40-90% of the blade height H. Further, the cross-section of the blade along the length direction adopts the center-of-gravity stacking structure to construct a thr...

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Abstract

The invention discloses a compressor rotor blade meeting both pneumatic and strength requirements. The whole compressor rotor blade is of a streamline profile. The profile is composed of an inner hook face and an outer hook face opposite to the inner hook face and comprises a lower half blade, a middle part and an upper half blade along the main axis. The inner hook face is in a concave shape. The concave degree is gradually decreased from bottom to top. The outer hook face is in a convex shape, and the convex degree is gradually decreased from bottom to top. The cross section curvature of the middle part is zero. Movable blade inlet and outlet airflow angles are matched and blade profile mean camber line second derivatives are reasonably and optimally matched, so that the blade profile cross section mean camber line curvature continuity is ensured, blade pneumatic loads are recombined, the movable blade channel internal shock wave structure and separation flowing obtained after shock wave and blade suction surface angle region secondary flow are effectively controlled, diffusion blade grating pneumatic losses are lowered, and the stable working range of a compressor is enlarged; the obtained novel rotor blade structure meets the actual pneumatic and strength requirements, and has the good engineering application value.

Description

technical field [0001] The invention belongs to the field of aerodynamic design of impeller machinery, and in particular relates to a compressor rotor blade which takes into account both aerodynamics and strength. Background technique [0002] The development requirement of high thrust-to-weight ratio of modern aerodynamic system puts forward extremely high requirements for its main aerodynamic components - fan / compressor. This requires that the fan / compressor not only has a large flow rate, a high stage pressure ratio and efficiency, but also must have a relatively wide and stable working range under all working conditions. A significant increase in the load level of the fan / compressor unit will inevitably lead to an increase in the Mach number of the rotor blade tip. At the same time, due to the accumulation of low-energy fluid in the corner area of ​​the shock wave and the suction surface of the blade, the expansion pressure and strong shear will cause large-scale separat...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/26
CPCF04D29/26F05D2240/301
Inventor 杨显清陈焕龙关国锋游志全石丹
Owner 友铂空天动力(深圳)有限公司
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