Design/Construction/Operation of Experimental Apparatus for Performance Evaluation of Heat Exchanger

In this study, we designed, constructed, and operated an experimental facility to realize the inlet conditions to evaluate a turbine exhaust heat exchanger of a space launch vehicle. The entire facility consists of a steam generator for high-temperature fluid simulation and a flow stabilizer to ensure uniform flow. The inlet conditions at the target heat exchanger are a pressure of 0.22 MPa and a temperature of 773 K. For a 10-s combustion test at a pressure of 0.22 MPa, the resulting temperature was 850 K. The pressure was measured with 7 % error, and the temperature was uniformly realized at about 10 % higher than the target temperature. Based on this, it is expected that performance tests of the pressurized heat exchanger will be conducted in the future.