The present invention belongs to the field of the temperature measurement technology, and specifically relates to a nozzle section chamber wall temperature gradient measurement module of a liquid-propellant rocket engine combustion chamber. The module provided by the invention has an annular structure, and comprises an annular 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 annular 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 cross 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.