Experimental device of variable-structure rocket-based-combined-cycle combustion chamber

Abstract

The invention discloses an experimental device of a variable-structure rocket-based-combined-cycle combustion chamber. The experimental device comprises a combustion chamber isolation section being ahollow shell with two open ends and a combustion chamber expansion section being a hollow shell with two open ends. The combustion chamber expansion section is encircled by a top plate assembly, a side plate and a bottom plate; and the front end of the combustion chamber expansion section is communicated with the outlet end of the combustion chamber isolation section. The top plate assembly includes a fixed plate, a translation top plate, and a rotating top plate. The front end of the fixed plate is fixedly connected with the top plate of the combustion chamber expansion section; and the fixedplate is inclined upwardly from the front to back. The front end of the translation top plate is in sliding connection with the lower surface of the front section of the fixed plate; and the translation top plate can slide back and forth along the front section of the fixed plate to change the expansion ratio of the combustion chamber. The front end of the rotating top plate is hinged to the tailof the translation top plate and a rotating shaft can be arranged at the hinged part; and the rear end of the rotating top plate can rotate in a direction away from or close to the fixed plate so asto change the geometric throat area of the combustion chamber. Therefore, the adjustment of the configuration of the combustion chamber under different incoming flow Mach number conditions can be realized; and a problem of dynamic sealing in the process of adjusting the structure of the combustion chamber is solved.

Description

technical field [0001] The invention belongs to the technical field of a rocket-based combined power circulation combustion chamber, and in particular relates to an experimental device for a variable-structure rocket-based combined power circulation combustion chamber. Background technique [0002] The rocket-based combined power cycle (Rocket-Based-Combined-Cycle, RBCC) engine is a combined propulsion system for multi-task work in a wide speed range, which combines a rocket engine with a high thrust-to-weight ratio and low specific impulse with a rocket engine with a low thrust-to-weight ratio and high specific impulse. Chong's dual-mode ramjet engine is organically integrated in a flow channel, which can realize the aircraft from zero-speed take-off to hypersonic flight, and is one of the main power solutions for future reusable aerospace transportation and near-space vehicles. The RBCC engine mainly experiences four working modes according to different flight states, name...

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide a variable structure rocket-based combined power cycle combustor experimental device for the above-mentioned deficiencies in the prior art, to realize the adjustment of the configuration of the combustor under different incoming flow Mach numbers, and to solve the problem of combustion Dynamic sealing problem in chamber structure adjustment process

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