APPARATUS FOR MEASURING THE TEMPERATURE OF THE NOZZLE OF A ROCKET ENGINE

FIELD: measuring.SUBSTANCE: invention relates to methods for functional monitoring and diagnostics of the condition of complex pneumohydraulic objects, e.g., liquid rocket engines (LRE). Proposed is an apparatus for measuring the temperature of the nozzle of a rocket engine, containing a nozzle made of electrically conductive and heat-resistant materials, applied to the inner surface whereof is a layer of material with a low output operation, wherein the emission layer on the surface of the nozzle is formed by a cathode, an anode is located at the outlet of the nozzle, wherein the anode is electrically series-connected with the cathode via an electric power source, the anode is in mechanical contact with the nozzle via an electrical insulation layer, the emission layer is made in the form of a ring with a thickness of 5 to 10 mm, in the critical section area, in the electrical circuit between the anode and the voltage source, a measuring complex is located, wherein an apparatus for storing and supplying substances with a low ionisation potential is added in the form of a nozzle for supplying substances with a low ionisation potential, located in the combustion chamber before the critical section of the nozzle and hydraulically, via a pipeline and an adjustable valve, connected with the tank for storing substances with a low ionisation potential (SLIP), wherein the adjustable valve is electrically connected with the signal output of the measuring complex, the outlet of the nozzle for supplying substances with a low ionisation potential is located flush with the surface of the LRE wall.EFFECT: accuracy of measurement of the temperature of the monitored surface with a high reaction rate; also realised is a possibility of long-term operation in extreme temperatures due to the surface cooling.1 cl, 1 dwg Изобретение относится к способам функционального контроля и диагностирования состояния сложных пневмогидравлических объектов, например жидкостных ракетных двигателей (ЖРД). Предлагается устройство для измерения температуры сопла ракетного двигателя, которое содержит выполненное из электропроводящих и жаропрочных материалов сопло, на внутреннюю поверхность которого нанесен слой из материала с низкой работой выхода, при этом эмиссионный слой на поверхности сопла образуют катод, на выходе из сопла расположен анод, причем анод электрически последовательно связан с катодом через источник электроэнергии, анод находится в механическом контакте с соплом через слой элек