Scramjet engine air inlet compression technology based compressed rotor

Abstract

The invention disclosed a scramjet engine air inlet compression technology based compressed rotor. The scramjet engine air inlet compression technology based compressed rotor comprises a hollow shaft, a roulette component assembled synchronically and rotatably with the hollow shaft and an outer casing sleeving the roulette component; a plurality of spiral partitions are evenly distributed on the surface of the outer wall of the outer roulette flange of the roulette component, and installation angles of the spiral partitions are identical; one flow path is formed in the gap between every two neighboring spiral partitions, and an airflow compression section, a throat isolation section and a triangular exit extension section are sequentially arranged on each airflow compression section from the inlet end to the outlet end; the airflow compression section is a compressed air path which is arranged in a manner that the radial clearance is narrowed gradually; the throat isolation section is a equal-area path arranged in a manner that the radial clearance is remained unchanged; the triangular exit extension section is an air path arranged in a manner that the radial clearance is remain unchanged while the inner circumferential cylindrical surface is triangular. By the above technical scheme, the fluid is compressed through a curve shock-wave system, the supercharge ratio is high, and the compressed rotor is integrally structurally simple and compact and high in reliability.

Description

technical field [0001] The invention relates to the field of gas turbines, in particular to a ram compression rotor applied to various gas turbines based on the scramjet engine intake channel compression technology. Background technique [0002] The compression system, namely the compressor, is one of the three major components of a gas turbine. Its function is to compress the airflow entering the engine to obtain air at a suitable temperature and pressure. The pressure ratio and compression efficiency of the compressor will directly determine the cycle efficiency and power of the gas turbine, while its volume and weight will largely affect the power-to-weight ratio of the gas turbine. At present, the airflow compression methods commonly used in gas turbines mainly include axial flow compression, centrifugal compression and hybrid compression. Axial flow compression single-stage compression has high efficiency, wide application, and mature technology, but its single-stage p...

AI Technical Summary

Problems solved by technology

Axial flow compression has high single-stage compression efficiency, wide application, and mature technology, but its single-stage pressure ratio is low, multi-stage compression is required to achieve high pressure ratio, the volume and weight of the compression system are large, and the total compression efficiency is reduced; centrifugal compression single-stage compression Relatively high, relatively stable performance, but its efficiency is low

The above two airflow compression methods can also be used in combination, but it has no essential effect on improving the power-to-weight ratio of the gas turbine

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