Pre-cooling air-breathing type variable cycle engine

Abstract

The invention discloses a pre-cooling air-breathing type variable cycle engine and relates to the reusable pre-cooling air-breathing type variable cycle engine applied to aeronautics and astronautics devices. The engine mainly consists of a pre-cooler, a turbine engine, a super combustion chamber and a super combustion ramjet engine, wherein the pre-cooler and the super combustion chamber form a subsonic combustion ramjet engine; a turbine subsonic combustion ramjet engine is connected with the super combustion ramjet engine in parallel; working states of the turbine subsonic combustion ramjet engine and the super combustion ramjet engine are selected by adjusting a switching adjusting device, so that the working modal of the whole engine is controlled. The pre-cooler can reduce an inlet gas flow temperature of a super combustion chamber, can increase the efficiency of the super combustion chamber, can expand the working range of a subsonic combustion punching modal, and can make up insufficient thrust force when turbine subsonic combustion ramjet engine is transferred to the super consumption ramjet engine, so that the pre-cooling air-breathing type variable cycle engine has the advantage that the transfer class of a combined engine is stably transferred.

Description

technical field [0001] The patent of the present invention relates to a new type combined engine, in particular to a reusable pre-cooled air-breathing variable cycle engine applied to aircraft in the atmosphere. Background technique [0002] Existing air-breathing power systems flying in the atmosphere mainly include turbine engines and ramjet engines. Aero-engines are characterized by high specific impulse, but they are difficult to be used in the power system of aircraft with a height of 20km or a speed of Mach 3.0 or more. The bottleneck of research and development; the ramjet engine is suitable for higher flight Mach number and has higher specific impulse, but the flight maneuverability is poor, and the initial speed problem needs to be solved with the help of a booster. Therefore, the combination of turbo and ram can make up for their respective shortcomings. The turbo combined engine is suitable for hypersonic aircraft with a Mach number of 5-8, and it is one of the pr...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a pre-cooled air-breathing variable cycle engine for the bottleneck problem of low transition state efficiency in the current turbo-ram combination, that is, the pre-cooler is used to cool the incoming air, and the super combustion chamber can be enlarged efficiency, expand the working range of the sub-combustion ramjet mode, and make up for the lack of thrust when the turbo sub-combustion ramjet transitions to the scramjet mode, so as to realize the smooth transition from the turbine engine to the ramjet engine

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