Air turbine rocket stamping combined propulsion system

Abstract

The invention relates to an air turbine rocket ramjet combined propulsion system which comprises a core engine of an air turbine rocket engine, the core engine is arranged in a central flow channel of an air turbine rocket, a cartridge receiver is arranged on the periphery of the core engine, and a ramjet isolation section flow channel is arranged in the cartridge receiver. A first mode conversion valve is arranged at the front end, corresponding to an inlet of the central runner, of the stamping isolation section runner, and a second mode conversion valve is arranged at the tail end, corresponding to an outlet of the gas compressor, of the stamping isolation section runner; a first combustion chamber is arranged behind the second mode conversion valve; a turbine outlet of the core machine is provided with a second combustion chamber, and the outer wall of the second combustion chamber is provided with an adjustable throat used for guaranteeing the combustion state of the engine; by means of the series connection mode, the ATR and the scramjet engine are organically combined together, the performance of the combined engine in the rotating mode is improved, the flight speed range of the engine is widened, and the performance of the engine in each mode is enhanced.

Description

technical field [0001] The invention relates to an aerospace propulsion system, in particular to a turbo rocket stamping combined propulsion system. Background technique [0002] The mission requirements of the aircraft are becoming more and more complex, and the requirements for the propulsion system of the aircraft are becoming more and more stringent. The engine must work on the flight profile of large airspace, high speed and wide speed range to achieve the goal of fast, economical and repeatable use. . One of the ways to improve the wide speed range of the combined engine is to organically combine two engines with a wide speed range. At the same time, the working ranges of the two engines have a large overlapping part, and the performance of the two engines is relatively high in the overlapping part. high. Due to the complexity of the flight mission, the engine requires a high thrust-to-weight ratio, low fuel consumption, high thrust, simple structure, zero-speed take...

AI Technical Summary

Problems solved by technology

Two kinds of engines work in different modes, the working speed range of components is wide, the working environment changes greatly, and the compatibility of components is high, which puts forward high requirements for the design of the engine. The existing turbine-based combined engine is in the rotating mode Sometimes there is a problem of insufficient thrust, or relatively weak performance, etc., but the traditional engine adopts a fixed geometry method, and it is difficult to match the engine. In this way, the working speed range and range of the engine are relatively small, which is suitable for wide speed range and The flight process in a large airspace creates great constraints, and at the same time restricts the closure of the flight mission

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