Journal
TRANSACTIONS OF THE KOREAN SOCIETY OF MECHANICAL ENGINEERS B
Volume 43, Issue 5, Pages 313-321Publisher
KOREAN SOC MECHANICAL ENGINEERS
DOI: 10.3795/KSME-B.2019.43.5.313
Keywords
Turbine Exhaust; Heat Exchanger; Pressurant; Steam Generator; Gas Generator
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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.
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