Structural layout of a multi-parameter optical measurement platform for a supersonic combustion chamber

Abstract

The invention discloses a structural layout of a multi-parameter optical measurement platform for a supersonic combustion chamber, which is composed of a closed dustproof room, a shockproof platform, a dust removal and dehumidification ventilator, and a thermostat; the closed dustproof room is a closed space with a sandwich structure. The interlayer is provided with several chamber wall bumps and filled with sound-absorbing materials, which effectively blocks the influence of external noise. The dust removal and dehumidification ventilator and thermostat are placed in a closed dustproof room to provide protection for the working environment of optical instruments. The anti-vibration platforms are respectively placed on the left, right and bottom of the measurement area to prevent vibration from affecting the optical path and causing measurement errors. The flat optical glass is respectively installed on the wall of the airtight dust-proof room to provide the necessary optical circuit window for optical measurement. A variety of optical instruments are used to measure various parameters in the supersonic combustion chamber. While obtaining various parameters of the supersonic combustion chamber, the accuracy of the measurement data is improved, and the service life of the equipment and the experimental efficiency are improved.

Description

technical field [0001] The invention belongs to the technical field of aero-engine testing, and in particular relates to the structural layout of a multi-parameter optical measurement platform for a supersonic combustion chamber. Background technique [0002] The supersonic combustion chamber is one of the core components of a hypersonic vehicle. Because it works under the extreme conditions of high temperature and high pressure, the stagnation temperature of the incoming air is about 860K at Mach number 4, and about 1640K at Mach number 6. , and at Mach number 8 it is about 2580K; the gas temperature after combustion in the engine is higher, at Mach number 4, 6, 8 respectively about 2500K, 2700K, 3100K; the gas flow velocity inside the combustion chamber can reach 1000m / s or more, so it is very difficult to measure the internal parameters when it is working. At present, the main means of measuring the gas phase combustion system is to use the plug-in probe, but the distur...

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Problems solved by technology

[0005] In order to avoid the shortcomings of the existing technology and overcome the problems of poor actual measurement environment conditions, small measurement range and single measurement parameters, the present invention proposes a structural layout of a multi-parameter optical measurement platform for supersonic combustion chambers. The optical instrument measures various parameters inside the supersonic combustion chamber, and solves the stringent requirements for the working environment of related optical instruments when measuring the internal parameters of the supersonic combustion chamber and the wind tunnel test and extremely harsh measurement of the supersonic combustion chamber The contradiction of the environment, while obtaining various parameters of the supersonic combustion chamber, improves the accuracy of the measurement data, improves the service life of the equipment and the experimental efficiency

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