Centripetal impeller of a gas turbine engine

Abstract

The invention discloses a centripetal impeller for a gas turbine engine, which comprises an impeller disk (1) and blades (2). The blades (2) are arranged on the surface of the impeller disk (1), and extend to a rim (3) outside the impeller disk (1); the impeller disk (1) at the backs of the blades (2) is provided with a pocket (4); at least two circular arc surfaces are formed in the pocket (4). The pocket is processed at the position at the back of the impeller to reduce a centrifugal load borne by an impeller center so as to reduce stress. Due to the structural characteristics of the centripetal impeller, the pocket cannot be excessively deep dug and the fillet radius also cannot be excessively large; the adoption of a multi-section circular arc structure of the pocket can effectively solve the problem of limitation of the fillet radius; aiming at the pocket, the multi-section circular arc structure is adopted, a large circular arc radius is adopted in a region with a large stress and a small circular arc radius is adopted in a region with a small stress. According to the novel structure, the stress can be greatly reduced in a small space range and service life is prolonged.

Description

technical field [0001] The invention relates to the technical field of gas turbine engines, in particular, to a centripetal impeller of a gas turbine engine. Background technique [0002] The centripetal impeller has the advantages of high falling pressure ratio, strong working ability, high performance under small flow rate, few parts, and low manufacturing cost. At present, it has been widely used in small and medium-sized aviation power auxiliary devices and turbo pumps for rockets. and automotive turbochargers. [0003] The working speed of the centripetal impeller is relatively high, generally above 50,000r / min, and the radius of the flow channel is relatively large, and the centrifugal load is large; in addition, as the hot end part of the turbine, its working temperature is relatively high, and the working temperature of the current advanced centripetal impeller is generally at 700 ° C or above. Based on the above two reasons, the centrifugal and thermal loads of t...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a centripetal impeller of a gas turbine engine to solve the technical problems of the centripetal impeller, such as high centrifugal and thermal loads, high stress, and short service life.

Images