Centrifugal compressor diffusor structure with blades being integrated with case and hub

Abstract

The invention discloses a centrifugal compressor diffusor structure with blades being integrated with a case and a hub. The centrifugal compressor diffusor structure with the blades being integrated with the case and the hub belongs to the technical field of middle-small aero-engine compressors, and is characterized in that a radial diffuser and an axial diffuser are connected into a whole, and aleading edge is designed into a sharp edge, so that the loss is reduced, and the outer diameter of each diffuser is reduced; and the blades are further integrated with the case of each diffuser and the hub, so that the distortion degrees of the blades of each diffuser are reduced, and the blades are convenient to design and process. The centrifugal compressor diffusor structure with the blades being integrated with the case and the hub provided by the invention can be directly applied to small aero-engines, the outer diameter of the engine can be reduced without increasing the processing costand reducing the compressor performance, and the thrust-weight ratio of the engine is improved.

Description

Technical field [0001] The invention belongs to the technical field of small and medium aeroengine compressors, and relates to a centrifugal compressor diffuser structure, in particular to a centrifugal compressor diffuser structure in which blades, casing and hub are fused, and can be installed at the inlet of the diffuser Under the condition of the same diameter, the maximum outer diameter of the diffuser is reduced, and the distortion of the pressure surface and suction surface of the diffuser blade is also reduced. It is especially suitable for small and medium-sized aero-engine high-pressure centrifugal compressors. Background technique [0002] Centrifugal compressors have been widely used in small gas turbines and small and medium aeroengines due to their advantages of high single-stage pressure ratio, wide working range, simple structure and high reliability. As the pressure ratio of the centrifugal compressor increases, the unevenness of the airflow at the outlet of the ...

AI Technical Summary

Problems solved by technology

At the same time, in order to reduce the frontal area of ​​the engine and increase the thrust-to-weight ratio of the engine, it is necessary to reduce the radial size of the engine to the greatest extent. With the reduction of the outer diameter of the engine, the length of the radial diffuser of the centrifugal compressor decreases, and the diffuser The sharp increase of the diffuser load makes the flow channel separation in the vane channel very easy, resulting in an increase in the loss in the diffuser, making the design of the diffuser more difficult

[0003] In the prior art, by making the radial diffuser and the axial diffuser into an integrated structure (such as CN201410453415.4, CN200810196137.3, etc.), to reduce the gap between the radial diffuser and the axial diffuser The mixing loss in the turning section is conducive to reducing the maximum outer diameter of the diffuser under the premise of maintaining the same characteristics of the compressor, but the integrated diffuser blades will also change from the radial direction to the axial direction. Deflecting from the pressure surface to the suction surface, when the radial height of the diffuser is small, the diffuser blades will be twisted more seriously, resulting in greater difficulties in the design, shape and processing of the diffuser blades

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