A two-stage precompressed mid-arc airfoil structure

Abstract

A two-stage pre-compressed mid-arc airfoil structure, the mid-arc airfoil forms various types according to the different Mach numbers of the inlet, Ma=0.8~1.2 in the transphonic region, adopts double-arc airfoil, and the midline is a The whole section of arc; Ma=1.2‑1.4 in the supersound area, adopts multi-arc leaf shape, the center line is composed of two sections of arc, and the slope of the two arcs at the transition point is equal. When the Mach number exceeds 1.4, the shock loss is intensified, and the back and front section of the blade is made into a concave shape to reduce the Mach number of the wave front, control the shock wave intensity, and reduce the shock wave loss, that is, the blade shape is a pre-compressed blade shape. Taking the maximum pre-compression point of the relative bending angle of the airfoil as the dividing point, the middle arc is divided into two sections, the front and rear sections adopt different relative bending angle changing rules. The invention has the advantages of strong pressurization capacity, large flow capacity, small lag angle, larger pre-compression amount and length of pre-compression section, and is suitable for supersonic rotor design.

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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