Two-section type pre-compression central arced curve blade profile structure

Abstract

Provided is a two-section type pre-compression central arced curve blade profile structure. Central arced curve blade profiles have multiple types according to different inlet Mach numbers, the dual-arc blade profile is adopted in a transonic region with the Ma being equal to 0.8-1.2, and a whole arc serves as the central line; the multi-arc blade profile is adopted in a supersonic region with the Ma being equal to 1.2-1.4, the central line is composed of two arcs, and the slopes of the two arcs are identical at a transition point. When the Mach number is larger than 1.4, shock wave loss increases, the front section of the blade back is concave so as to reduce the wave-front Mach number, the shock wave strength is controlled, and the shock wave loss is reduced, namely the pre-compression blade profile is adopted. The central arced curve is divided into a front section and a rear section with the maximum pre-compression point of a blade profile relative bend as the demarcation point, and different relative bend changing laws are adopted by the front section and the rear section respectively. The two-section type pre-compression central arced curve blade profile structure has the advantages that the pressurizing capacity is high, the flow capacity is high, the deviation angle is small, the higher pre-compression quantity and the larger pre-compression section length are selected, and the two-section type pre-compression central arced curve blade profile structure is suitable for the design of hypersonic-speed rotors.

Description

technical field [0001] The invention relates to the field of fans and aerodynamics, in particular to a two-stage precompressed arc blade structure. Background technique [0002] The arc of the blade shape is the basis of the shape of the blade and plays a decisive role in the performance of the blade shape. When designing the blade shape, the matching arc of the blade shape should be adopted according to the corresponding Mach number of the different incoming flow. At present, most of the mid-arc forms are suitable for subsonic, transonic, and supersonic flow fields with a Mach number lower than 1.5. For the supersonic rotor design with a Mach number exceeding 1.5, there is no suitable mid-arc blade in engineering. Type exists, while the application of conventional blade type shows shortcomings such as insufficient boosting capacity and small flow capacity, which cannot meet the design requirements of high-load fan rotor blades. Contents of the invention [0003] The purp...

AI Technical Summary

Problems solved by technology

At present, most of the mid-arc forms are suitable for subsonic, transonic, and supersonic flow fields with a Mach number lower than 1.5. For the supersonic rotor design with a Mach number exceeding 1.5, there is no suitable mid-arc blade in engineering. Type exists, while the application of conventional blade type shows shortcomings such as insufficient boosting capacity and small flow capacity, which cannot meet the design requirements of high-load fan rotor blades

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