A supersonic detonation engine and its propulsion system

Abstract

The invention discloses a propulsion system which comprises an air inlet channel, a combustion chamber and an expansion spraying pipe connected with the combustion chamber. A first hot jet flow spout allowing spraying of a hot jet flow is formed in the upper wall surface of the combustion chamber, a second hot jet flow spout allowing spraying of the hot jet flow is formed in the lower wall surface of the combustion chamber, after spraying the hot jet flows, the first hot jet flow spout and the second hot jet flow spout can induce a supersonic velocity incoming flow to form two strands of oblique detonation waves, and the two strands of oblique detonation waves can intersect in the middle of the expansion spraying pipe. According to the propulsion system provided by the invention, the first hot jet flow spout and the second hot jet flow spout are formed in the combustion chamber, the hot jet flows sprayed from the two hot jet flow spout induces the incoming flow to form the stable oblique detonation waves, and the oblique detonation waves produce regular reflection, so that the action of the detonation waves and a boundary layer is avoided, meanwhile, full combustion of incoming flow premixed gas is guaranteed, after combustion through the double oblique detonation waves, heat is released rapidly, expansion occurs to produce thrust, and the combustion efficiency is improved. The invention further discloses a supersonic velocity detonation engine comprising the propulsion system.

Description

technical field [0001] The invention relates to the field of detonation engine equipment, in particular to a propulsion system. In addition, the present invention also relates to a supersonic detonation engine comprising the above propulsion system. Background technique [0002] With the development of hypersonic vehicles, the efficiency of the propulsion system has become one of the bottlenecks restricting the further improvement of engine thrust, while the detonation combustion thermodynamic cycle has high efficiency and fast heat release, and the supersonic propulsion system based on detonation combustion has a compact layout and a simple structure , therefore, detonation-based engines can be used as a potential solution for hypersonic propulsion systems. [0003] Under hypersonic conditions, the detonation combustor organizes combustion through the slope-induced detonation method. However, since the existing detonation-based engine considers the slope-induced detonation...

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Problems solved by technology

[0003] Under hypersonic conditions, the detonation combustor organizes combustion through the slope-induced detonation method. However, since the existing detonation-based engine considers the slope-induced detonation wave formation method to organize the detonation combustion, the oblique detonation wave directly Acting on the inner wall of the expanding nozzle, it interacts with the boundary layer on the wall of the expanding nozzle, causing the oblique detonation wave to propagate forward along the boundary layer, and the boundary layer has a greater influence on the oblique detonation wave. Detonation, resulting in greater aerodynamic drag and aerodynamic heat

[0004] At the same time, in the propulsion system in the prior art, the combustion chamber and the expansion nozzle are arranged separately. Since the combustion chamber needs to mix fuel, the length of the combustion chamber is generally long, resulting in a large volume of the entire propulsion system and a complicated structure of the engine.

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