A kind of compressor with ellipsoid convex structure leading edge blade

Abstract

The invention aims to provide a gas compressor with a front edge blade of a spheroid convex structure. The gas compressor comprises a receiver, a hub installed in the receiver, and blades mounted on the hub; all blades are formed to be a blade grid; the front edges of the blades are provided with the spheroid convex structures aligned along the blade height direction at intervals, the length of a long shaft of the spheroid convex structure is 4-7 times of the diameter of the blade front edge, and the length of a short shaft is 0.5-3 times of the diameter of the front edge; the length of the spheroid convex structure extended out of the blade front edge is 2-3.5 times of the diameter of the blade front edge. By using a specific three-dimensional front edge structure, a local three-dimensional flow pipe shape is structured to inhibit the excessive expansion and flow; the gas compressor breaks through the design concept of a two-dimensional blade, obviously improves the front edge flowing, decreases the pneumatic loss of the blade grid, and increases an attack angle scale. Compared with the existing blade front edge technology of the gas compressor, the structure has obvious inhibiting effect to the flow loss at the end zone of the gas compressor.

Description

technical field [0001] The invention relates to a gas turbine, in particular to a gas turbine compressor. Background technique [0002] The improvement of the shape of the leading edge of the compressor blade is an important means to design and improve the performance of modern compressors. A large number of theoretical and experimental studies have shown that the change of the shape of the leading edge of the blade has a significant impact on the performance of the compressor, especially the change of the curvature of the leading edge. The boundary layer transition and development of the blade back arc at angle of attack play an important role. Experiments have shown that the loss caused by applying a thin layer to the front 10% of the blade is equivalent to the loss caused by applying a thin layer to the entire blade surface. Due to the sudden change of curvature at the transition between the leading edge structure of the traditional circular compressor and the profile li...

AI Technical Summary

Problems solved by technology

Due to the sudden change of curvature at the transition between the leading edge structure of the traditional circular compressor and the blade shape line, it is very easy to trigger the separation of the boundary layer at the leading edge of the blade, resulting in additional local losses that can reach about 30% of the blade shape loss

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