TY - GEN
T1 - Starting characteristics of hypersonic pre-cooled turbojet inlet
AU - Kojima, Takayuki
AU - Taguchi, Hideyuki
AU - Kobayashi, Hiroaki
AU - Sato, Tetsuya
N1 - Publisher Copyright:
© 2015, AIAA American Institute of Aeronautics and Astronautics. All rights reserved.
Copyright:
Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2015
Y1 - 2015
N2 - In this study, bypass door area for the Hypersonic Precooled Turbojet Engine to restart the variable intake is estimated. Total pressure recovery and mass capture ratio of the variable air intake is acquired by the supersonic wind tunnel testing of the half scale intake model. Pressure loss and temperature effectiveness of the precooler is acquired by direct connect firing tests of the engine. Using these results, area of the bypass door by which the intake can start is estimated. The bypass door area to restart the intake depends on the precooler’s cooling capability. If the engine runs on liquid hydrogen, area of the bypass door is 1800mm2~2000mm2(Abyp_eng/A0=0.26~0.29). If the liquid nitrogen is used for the coolant of the precooler, area of the bypass door is 2600mm2~2700mm2(Abyp_eng/A0=0.37~0.39).
AB - In this study, bypass door area for the Hypersonic Precooled Turbojet Engine to restart the variable intake is estimated. Total pressure recovery and mass capture ratio of the variable air intake is acquired by the supersonic wind tunnel testing of the half scale intake model. Pressure loss and temperature effectiveness of the precooler is acquired by direct connect firing tests of the engine. Using these results, area of the bypass door by which the intake can start is estimated. The bypass door area to restart the intake depends on the precooler’s cooling capability. If the engine runs on liquid hydrogen, area of the bypass door is 1800mm2~2000mm2(Abyp_eng/A0=0.26~0.29). If the liquid nitrogen is used for the coolant of the precooler, area of the bypass door is 2600mm2~2700mm2(Abyp_eng/A0=0.37~0.39).
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U2 - 10.2514/6.2015-3595
DO - 10.2514/6.2015-3595
M3 - Conference contribution
AN - SCOPUS:85088195183
SN - 9781624103209
T3 - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
BT - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
PB - AIAA American Institute of Aeronautics and Astronautics
T2 - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
Y2 - 6 July 2015 through 9 July 2015
ER -