Centrifugal gas compressor impeller with high-pressure ratio

Abstract

The invention discloses a centrifugal gas compressor impeller with a high-pressure ratio. The impeller is composed of blades and a blade disc, the blades are of distortion structures, the upper edges of the blades are in straight line shapes, the lower edges of the blades are in rear bending line shapes, and the outer edge of the axial section of the intersecting line of the blades and the blade disc is of a curve structure. The width of the blades on the edge of an impeller is large, the upper edges of the blades are located in the same plane, the blade and impeller windward plane attack angle is 25 to 75 degrees, the axial length of the blades is the same with the radius length of the blade disc, the windward face is an air inlet, and the air inlet amount is obviously improved. The gap between the blades is small, when the impeller rotates, gas is extruded into a runner, in the extrusion process, gas is pressurized, the gas flowing loss is small, the pressurizing effect is good, due to the fact that the width of the blades on the edge of the impeller is large, the blades are high in work doing capacity, and the pressure ratio is increased; and the upper edges of the blades are in straight line shapes, the air inlet efficiency is high, the impact is small, the lower edges of the blades are in rear bending line shapes, the flowing of the airflow on the outlet is uniform, and the flowing losses in a diffuser and a volute are small.

Description

technical field [0001] The invention relates to the technical field of gas turbines and impeller machinery, in particular to a centrifugal compressor impeller with a high pressure ratio. Background technique [0002] Single-stage centrifugal compressors are widely used in the structural design of small gas turbines. Generally, gas turbines with a power of 100kW to 5MW can adopt this structure. Especially for the application of megawatt-level power segment, the single-stage compressor has the characteristics of simple structure, small size, convenient maintenance, low failure rate, long life and high reliability. But at the same time, in order to ensure the realization of the design power index of the gas turbine, the compressor needs to have high pressure ratio parameters. For the impellers of gas turbine compressors of the same power range independently developed in China, the maximum design pressure ratio can only reach 4.3, while the pressure ratio of foreign single-stag...

AI Technical Summary

Problems solved by technology

Although the rectification and pre-compression of the inlet impeller section are enhanced, the inlet flow area is increased, the fluid flow rate is increased, and the airflow loss is reduced, which is beneficial to obtain a higher initial pressure airflow at the inlet impeller section, but the centrifugal compressor has not been improved. In terms of radial pressurization capacity, there are gas turbine compressor impellers of the same power range in the prior art, and the highest design pressure ratio is low; the centrifugal compressor has the defect of insufficient air intake, which will lead to surge, stable and efficient work The area is narrow, which is not conducive to the work done by the blades on the gas, and it is difficult to pressurize in a single stage

Images