Axial-symmetry inner parallel turbine-based rotary detonation ramjet combined engine and control method

Abstract

The invention provides an axial-symmetry inner parallel turbine-based rotary detonation ramjet combined engine. An axial-symmetry layout mode is adopted, a turbine engine is located in the middle, a rotary detonation ramjet engine is located in an outer ring flow pass, and an air inlet passage lip cover moves parallelly to adjust the air inlet passage contraction ratio and flow capture; through aparallel moving mode converting device, three modes of the engine are converted; the front edge of a mode converter is located at the downstream of an air inlet passage throat, expansion-type ramjet and turbine flow passes are constructed, ending shock waves can be limited in the flow passes, and the coupling interference of the rotary detonation ramjet engine and the turbine engine crossing the flow passes under the common working state is shielded; and an adjusting mode of parallel moving of the lip cover and the mode converting device has the advantages of being easy to operate, easy to implement, high in operability / reliability, convenient to seal and the like.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to a combined engine. Background technique [0002] Relying on a single power source is difficult to meet the needs of space-space integration with wide speed range, wide airspace, and high-efficiency flight. Driven by this demand, combined propulsion devices based on various types of power have emerged as the times require, including turbine-based combined cycle engines (TurbineBased Combined Cycle-TBCC ), Rocket Based Combined Cycle-RBCC (Rocket Based Combined Cycle-RBCC) and Turbine / Rocket Based Combined Cycle-T / RBCC, etc. The core of the combined cycle engine is to give full play to the performance advantages of various engines within the working range of Mach number, expand the working range of the entire engine, and improve engine efficiency. [0003] Turbine-based combined-cycle engine (TBCC) can realize horizontal take-off and landing of aircraft, reuse, and has good economy,...

AI Technical Summary

Problems solved by technology

Slow combustion is a chemical reaction exothermic process dominated by diffusion phenomenon. The small component diffusion velocity and thermal diffusion velocity determine the slow combustion wave propagation velocity, generally in the order of m / s, and this isobaric exothermic process It is an entropy-increasing process, and the thermal efficiency is not high

[0005] Therefore, it is necessary to develop a new type of combined power scheme, which can not only effectively fill the "thrust defect" of the turbine-based combined cycle engine, but also avoid the problems of high integration, complex structure and control system of the turbo-assisted rocket-enhanced ramjet combined cycle engine

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