Distributed compression and cyclone ramjet engine

Abstract

The invention discloses a distributed compression and cyclone ramjet engine and aims to solve the problems that an existing ramjet engine cannot start by itself, and can work only by being accelerated to a certain speed by a roll booster, the existing ramjet engine is sensitive to changes in flight states, and when the existing ramjet engine is combined with a turbojet engine or a fanjet to be used as an aero-engine, the beneficial effects that the ramjet engine is simple in structure and the like are lost. The engine comprises turbine systems, a casing, a cyclone generator, a low-temperature heat exchanger, a guide blade, a stamping cone, an intermediate-temperature heat exchanger, a high-temperature heat exchanger and the like. Turbines are heated by heat exchange gas and pushed by cooling circulation, energy of stamping airflow is fully utilized, the circulation efficiency of the engine is effectively improved, cost is reduced, cyclone stamping is utilized, and the problems that the existing ramjet engine cannot be started at a low speed and cannot adapt to various work conditions are solved. The distributed compression and cyclone ramjet engine is ingenious in concept, reasonable in design and capable of achieving static starting of the engine and adapting to various work conditions, and good application prospects are achieved.

Description

technical field [0001] The invention relates to the field of aviation, in particular to the field of aeroengines, in particular to a distributed compression and swirl ramjet engine. Background technique [0002] With the development and application of modern aero-engine, it has gone through a hundred years of glorious history. For more than half a century, the technology of aero turbine engines has been continuously improved, and the performance level has been greatly improved. Among them, the thrust-to-weight ratio of the military engines in service in the world has been increased from 2 to 7-9, the total boost ratio has been increased to 25-45, and the fuel consumption rate has decreased from 1.0 to 1.2kg / (daN h) to 0.6~0.7kg / (daN·h). The thrust-to-weight ratio of the military engine under research reaches 9-11, and it has been put into use; the maximum thrust of the civil high bypass ratio turbofan engine has exceeded 57000daN, and the cruising fuel consumption rate has...

AI Technical Summary

Problems solved by technology

[0008] The purpose of the invention of the present invention is: for the existing ramjet engine cannot start by itself, the booster needs to be accelerated to a certain speed to work, and it is more sensitive to the change of the flight state, and it is combined with a turbojet engine or a turbofan engine as an aviation engine. When the engine is in use, m

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