Design study of turbine for pulse detonation combustor

Takayuki Kojima*, Nobuyuki Tsuboi, Hideyuki Taguchi, Hiroaki Kobayashi, Tetsuya Sato, Yu Daimon, Kazuaki Inaba

*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceedingConference contribution

12 Citations (Scopus)


This paper describes design study of the gas turbine engine using PDE as a main combustor of which hydrogen is used as a fuel. In the present analysis, exhaust gas condition of the simple PDE in which no turbine or other obstacles are installed which is estimated by CFD is referred as a turbine inlet condition. About 65 % of enthalpy drop at the exit of the PDE occurs during the exhaust of high temperature combustion gas behind the detonation wave. Furthermore, turbine adiabatic efficiency map of a conventional turbine is taken into account. Approximately, 51-80% of enthalpy drop through the turbine can be extracted as a turbine power. Partial filling of the PDE tube has an effect of smoothing the peak of U/C0.

Original languageEnglish
Title of host publicationCollection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Number of pages9
Publication statusPublished - 2007 Dec 10
Event43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference - Cincinnati, OH, United States
Duration: 2007 Jul 82007 Jul 11

Publication series

NameCollection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference


Conference43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Country/TerritoryUnited States
CityCincinnati, OH

ASJC Scopus subject areas

  • Space and Planetary Science


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