A vaned diffuser with a dovetail-shaped leading and trailing edge structure and its modeling method

Abstract

The invention discloses a vane diffuser with a swallow-tail leading and trailing edge structure as well as a modeling method of the vane diffuser. The vane diffuser comprises a diffuser wheel disc, a diffuser wheel cover, built-in radial diffuser blades and built-in axial diffuser blades, wherein the radial diffuser blades and the axial diffuser blades are uniformly distributed between the diffuser wheel disc and the diffuser wheel cover in the circumferential direction. The vane diffuser disclosed by the invention is creatively transformed from a conventional vane diffuser, and has the advantages of being convenient in modeling, low in cost and simple in machining; by adoption of special swallow-tail leading and trailing edges, the adaptive capacity of the vane diffuser to high-speed disorderly flow at the outlet of a centrifugal impeller can be improved, thereby greatly improving the efficiency and the steady operation margin of a high-pressure-ratio centrifugal compressor; through an anti-scale coating on the blades, scale deposition can be effectively reduced, enough air circulation area can be kept, and the flow friction can be reduced, thereby solving the surge problem of the compressor and improving the safety of the compressor; and accordingly, the vane diffuser is particularly applicable to high-pressure-ratio centrifugal compressors of small- and medium-sized aero engines.

Description

technical field [0001] The invention belongs to the field of high-pressure ratio centrifugal compressors, and relates to a vane diffuser with a dovetail-shaped front and rear edge structure and a modeling method thereof. Background technique [0002] Due to the advantages of compact structure, high pressure ratio, high reliability, convenient manufacture, low cost, good manufacturability and wide stable working margin, centrifugal compressors have been widely used in small and medium-sized engines. In order to further improve the thrust-to-weight ratio / power-to-weight ratio of the engine and improve the performance under various flight conditions at high altitude, higher requirements are placed on the pressure ratio of the centrifugal compressor; The outlet width of the centrifugal impeller is very small, and the diffuser inlet is very close to the impeller outlet. There is a strong unsteady interaction between the two, which deteriorates the matching between the centrifugal...

AI Technical Summary

Problems solved by technology

However, for the tubular diffuser in which the radial diffuser and the axial diffuser are designed to be integrated, there is generally a phenomenon that the axial outlet air flow is extremely uneven along the circumferential direction, and the compressor surge problem caused by it is also It brings safety hazards to the application of compressors. In addition, the tubular diffuser also has problems such as difficult processing, high cost, and difficulty in guaranteeing processing accuracy.

Images