Tool for measuring gas-liquid two-phase heat flux density in rocket engine

Abstract

The invention provides a tool for measuring the gas-liquid two-phase heat flux density in a rocket engine, which comprises a temperature measurement base material and a circumferential heat insulationmaterial, and is characterized in that the temperature measurement base material is embedded into the circumferential heat insulation material; a plurality of thermocouples are pre-buried in a temperature measuring base material to serve as measuring points, the burying direction of the thermocouples is perpendicular to the airflow heat transfer direction in the rocket engine, the adjacent thermocouples are oppositely arranged in a staggered mode at equal intervals, and the working ends of all the thermocouples are located on the same straight line. Based on the thought of lumped capacitance,the measuring tool for dynamically measuring the gas-liquid two-phase heat flux density in the solid rocket engine in real time is designed, a temperature measuring base material is embedded into a circumferential heat insulation material, and a plurality of thermocouples are pre-buried in the temperature measuring base material to serve as measuring points; when the measuring points are used inparticle scouring or deposition positions in a rocket engine, the purpose of long-time survival in harsh environments such as high temperature, high pressure and the like of the engine can be achieved.

Description

technical field [0001] The invention relates to heat flow measurement technology, in particular to a tool for measuring gas-liquid two-phase heat flow density in a rocket engine. Background technique [0002] During the working process of the solid rocket motor, the violent combustion of the propellant will generate a high-temperature, high-speed gas flow of 2500-3900K, and the heat flow generated by the high-temperature gas will seriously ablate the thermal protection material of the engine. At the same time, the condensed phase particles in the combustion products will cause serious erosion and erosion to the submerged section and the convergent section of the nozzle, thereby greatly increasing the thermal load of the engine. In order to ensure that the rocket engine can maintain normal work under severe thermal environmental conditions, and that the spacecraft will not be burned due to the external heating environment during the ascent and reentry phases, it is necessary ...

AI Technical Summary

Problems solved by technology

Chen Zeshao and others introduced the lumped heat-melt transient radiation heat flow meter. The general radiation heat flow meter is designed by the heat balance method and cannot be used to measure the changing heat flow. The lumped heat flow meter is made of a thin copper sheet painted black on the surface The side of the head, the back of the copper sheet is insulated, affected by the thermal melting of the measuring head, its dynamic response characteristics are also relatively poor, so the transient heat radiation heat flux can be measured

[0006] To sum up, relevant research work has been carried out on the design of heat flow meters and the measurement of heat flow at home and abroad, but less is involved in the harsh environment such as high temperature and high pressure in solid rocket motors, and the test methods are quite different, and the influencing factors are more considered. less, leading to a large difference in conclusions

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