Ultrasonic ground experimental wind tunnel used for knocking combustion research

Abstract

The invention discloses an ultrasonic ground experimental wind tunnel used for knocking combustion research, and the wind tunnel provided by the invention comprises an ultrasonic premixing heater, an experimental section and a vacuum chamber, wherein the ultrasonic premixing heater comprises an injector 6, a preheating combustion chamber 1, an array nozzle module and a mixing section 3. The preheating combustion chamber adopts three components for combustion, and supplements oxygen or air after combusting hydrogen and air; and the preheating combustion chamber is designed to be in a colliding injection mode. The technique has the advantages that the combustion local high temperature can be effectively reduced, the thermal protection difficulty is reduced, the uniformity of flow field parameters such as gas mixture temperature, components and the like can be ensured, and the content of the oxygen in the gas mixture can be freely adjusted. The vacuum chamber is connected to the back of the experimental section, so that the back pressure of the experimental section can be reduced, and the design range of ultrasonic stream Mach numbers in the experimental wind tunnel is expanded.

Description

technical field [0001] The invention relates to a ground test system for the research of an air-breathing supersonic detonation engine used in aviation and aerospace, which can generate a supersonic premixed airflow with a maximum total temperature of 2000K, a total pressure of more than 2MPa and a wide range of equivalence ratios under simulated actual high-altitude conditions. Background technique [0002] Detonation combustion has the advantages of fast energy release rate and high thermal cycle efficiency, and has always attracted much attention in the field of propulsion. At present, supersonic pulse detonation engines and oblique detonation engines using detonation combustion have rapidly become the propulsion engine for hypersonic aircraft. Systematic research hotspots. The continuous high-enthalpy premixed supersonic flow heater is the key equipment for ground simulation test systems such as supersonic pulse detonation engines and oblique detonation engines. It conti...

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Problems solved by technology

The common problem of the above two kinds of experimental equipment is: the oblique detonation produced is moving at a high speed relative to the experimental observation, so the effective experimental time is very short, and it is difficult to study the dynamic process of detonation and development; because the static premixed gas is uniformly mixed in advance, In order to prevent safety problems such as spontaneous combustion and explosion, the static temperature of the premixed gas is usually room temperature

The biggest advantage of this experimental scheme is that it can keep the experimental piece static. The disadvantage is that: the shock tube technology is used, and the effective time of the experiment is very short, generally only 100μs to 200μs; although the pulse equipment can theoretically achieve a very high total enthalpy, in order to prevent Spontaneous combustion occurs in the secondary driving section, and the static temperature of the premixed gas after the shock wave is generally designed to be low, so the total enthalpy is limited to a certain extent; because the shock tube equipment needs to be accelerated through a long pipeline, the boundary layer becomes very thick, The quality of the premixed flow field is reduced, and the problem of spontaneous combustion in the high temperature zone of the boundary layer occurs

[0010] 1. High total enthalpy of premixed gas

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