Performance Analysis of SCO2 Reheat Closed Brayton Cycle Thermoelectric Conversion System for a Scramjet Engine
This study proposes a thermoelectric conversion system based on a supercritical carbon dioxide (SCO2) reheat closed Brayton cycle (RCBC) to address hypersonic flight vehicles power supply and thermal protection requirements. A coupled model consisting of the combustion chamber of a scramjet engine,a wall cooling channel,and a SCO2 RCBC is established to evaluate the system performance. The study compares the difference when the combustion chamber is coupled and uncoupled to the cooling channel,analyses the influence of the coolant inlet parameters on the thermal protection and power supply of the system. The results show that the thermoelectric conversion system is capable of providing 25.14 kW electrical power to a hypersonic flight vehicle while also providing thermal protection to the engine.
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