Coaxial centrifugal-oblique flow counter-rotating compressor

Abstract

The invention discloses a coaxial centrifugal-oblique flow counter-rotating compressor. The coaxial centrifugal-oblique flow counter-rotating compressor is characterized in that a centrifugal impellerand an oblique flow impeller are coaxially arranged along the axis of the compressor, a supporting casing is arranged on the back side region of the wheel disc of the oblique flow impeller, a transmission unit comprises a driving gear, a driven gear and an intermediate gear, the driving gear is fixedly arranged on the downstream shaft section of a driving rotor shaft of the centrifugal impeller,the driven gear is fixedly arranged on an oblique flow impeller shaft of the oblique flow impeller, the driven gear is indirectly meshed with the driving gear through the intermediate gear, the rotating direction of the centrifugal impeller is opposite to the rotating direction of the oblique flow impeller, and the rotating speed of the centrifugal impeller is higher than the rotating speed of theoblique flow impeller. Due to the fact that the two impeller rotors rotate in opposite directions, meanwhile the gas is compressed to do work, so that the centrifugal-oblique flow counter-rotating compressor has a single-stage compression ratio, small in diameter, light in weight, uniform in outlet air flow, small in axial airflow angle and the like, and is suitable for a high-efficiency and high-thrust-weight ratio / power-weight-ratio advanced aviation gas turbine engine compression system.

Description

technical field [0001] The invention relates to a counter-rotating compressor mainly composed of a centrifugal impeller and an oblique flow impeller opposite to the rotating direction. It specifically relates to a centrifugal-oblique-flow counter-rotating compressor that is driven by the same power source and rotates in opposite directions for small and medium-sized aviation gas turbine engines. The compressor has high single-stage pressure ratio, high efficiency, compact structure, small size and light weight It is suitable for the advanced aviation gas turbine engine compression system with high efficiency and high thrust-to-weight ratio / power-to-weight ratio. Background technique [0002] At present, the axial-centrifugal combined compressor or centrifugal compressor is widely used in small and medium-sized aero-engines. In the centrifugal compressor, the traditional structure such as figure 1 shown. Generally, a one-stage centrifugal compressor is composed of a centri...

AI Technical Summary

Problems solved by technology

This traditional centrifugal compressor has the advantages of high stage pressure ratio, compact structure, and wide stable working range; at the same time, it also has the disadvantages of large radial size (R2 / R1 is about 1.5 to 1.8) and low efficiency.

As the single-stage pressure ratio of the centrifugal compressor continues to increase, the load on the diffuser as a stator component increases sharply, resulting in deterioration of the internal flow of the diffuser and increased flow loss, which in turn seriously reduces the efficiency and stability of the traditional centrifugal compressor. The scope of work

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