Combustion chamber wall temperature gradient measurement module

Abstract

The present invention belongs to the field of the temperature measurement technology, and specifically relates to a cylindrical section chamber wall temperature gradient measurement module of a liquid-propellant rocket engine combustion chamber. The module provided by the invention has a flat plate structure, and comprises a planar pressure plate, five thermocouple sensors, springs, separation blades, heat insulation linings and support sleeves. A disc-shaped separation blade is welded at each thermocouple sensor, one end, at the upper portion of the separation blade, of the each thermocouple sensor passes through a support sleeve and a spring, the support sleeves are sleeved with the springs and sleeved with the planar pressure plate, and the portions, below the separation blades, of the thermocouple sensors penetrate into the heat insulation linings. According to the invention, the temperature of the inner wall structure of the cooling channel in a cylindrical section of the combustion chamber nozzle section may be measured, so that the parameters such as heat flow, gas wall temperature and outer wall temperature at the local place may be obtained.

Description

Technical field [0001] The invention belongs to the technical field of temperature measurement, and particularly relates to a temperature gradient measurement module for the cylindrical section wall of a liquid rocket engine combustion chamber. Background technique [0002] The working medium in the combustion chamber of the liquid rocket engine is a high-pressure gas above 3000K. In order to avoid ablation damage to the chamber wall, a milling channel is set between the inner and outer walls of the combustion chamber, and low-temperature fluid is introduced to cool the chamber wall structure. The heat flux through the cylindrical wall of the combustion chamber often reaches several tens of MW / m2, and the temperature difference that the structural materials bear is often more than several hundred K, and the working environment is very harsh. Therefore, understanding the heat transfer process in the thrust chamber is one of the most important prerequisites for a reasonable thermal...

AI Technical Summary

Problems solved by technology

However, because the rib width and wall thickness of the milling groove cooling structure are very thin (the rib width is usually 1-2mm, and the wall thickness is generally only 0.6-1mm), it is difficult to arrange ordinary sensors in the structure to affect the heat flux density, air wall temperature, etc. Parameters are directly measured

[0004] The traditional calorimetric scaling combustion chamber can only obtain the average heat flow in a certain section, but affected by the combustion process in the combustion chamber, the heat flow is not the same at different positions along the axial direction, so that the average heat flow cannot accurately reflect the actual local area. Heat flow, and due to the use of segmented water-cooled body parts, the structure of the coolant side, the heat transfer state is quite different from the full size, and the application error of this method is relatively large

Although the method of embedding thermocouple...

Images