A Coaxial Centrifugal-Diagonal 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 a diagonal flow impeller whose rotation direction is opposite to it. Specifically, it relates to centrifugal-diagonal flow compressors used in small and medium-sized aviation gas turbine engines driven by the same power source and rotating in opposite directions. The compressor has high single-stage pressure ratio, high efficiency, compact structure, small size and light weight. It is suitable for 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, small and medium-sized aero engines widely use axial-centrifugal combined compressors or centrifugal compressors. In a centrifugal compressor, the traditional structure is like figure 1 Shown. Generally, a one-stage centrifugal compressor consists of a centrifugal impeller, a radial diffuser ...

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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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