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Axial-flow compressor rotor blade

A compressor rotor and axial flow technology, which is applied to mechanical equipment, non-variable pumps, machines/engines, etc., can solve the problem of difficult balance between blade aerodynamic performance and strength

Pending Publication Date: 2021-06-08
友铂空天动力(深圳)有限公司
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The present invention provides an axial-flow compressor rotor blade structure in order to overcome the problem that it is difficult to balance the aerodynamic performance and strength of the blades in the existing related technologies.

Method used

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  • Axial-flow compressor rotor blade
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Embodiment Construction

[0018] In order to make the above objects, features and advantages of the present invention more comprehensible, specific embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0019] In the description of the present invention, it should be noted that in the description of the embodiments of the present application, the description of the term "some specific embodiments" means that the specific features, structures, materials or characteristics described in conjunction with the embodiments or examples are included in the In at least one embodiment or example of the invention. In this specification, schematic representations of the above terms do not necessarily refer to the same implementation or example. Furthermore, the specific features, structures, materials or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0020] see figure 1 , the present in...

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Abstract

The invention discloses an axial-flow compressor rotor blade which is integrally a streamline molded surface. The molded surface is composed of an inner curved surface and an outer curved surface opposite to the inner curved surface, and the molded surface comprises a lower half blade, a middle part and an upper half blade along the main axis of the molded surface. The inner curved surface is concave, and the concave degree of the inner curved surface is gradually reduced from bottom to top; the outer curved surface is convex, and the convex degree of the outer curved surface is gradually reduced from bottom to top; and the curvature of the cross section of the middle part is zero. According to the invention, through matching of inlet and outlet airflow angles of the moving blade and reasonable optimization matching of a second derivative of a blade profile mean camber line, curvature continuity of the blade profile mean camber line is ensured, so that the pneumatic load of the blade is recombined, a shock wave structure in a moving blade channel, separated flow after shock wave and secondary flow of a blade suction surface angle region are effectively controlled, the pneumatic loss of a diffusion cascade is reduced, and the stable working range of a gas compressor is expanded; and the obtained novel structure of the rotor blade meets the actual requirements in the aspects of pneumatics and strength, and has good engineering application value.

Description

technical field [0001] The invention relates to the field of turbomachinery aerodynamic design, in particular to an axial flow compressor rotor blade. 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 separation of the boundary layer. . In this way, not only the aerody...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/38
CPCF04D29/386
Inventor 李婷婷刘华坪杨显清
Owner 友铂空天动力(深圳)有限公司
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