Design study of turbine for pulse detonation combustor

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

研究成果: Conference contribution

6 被引用数 (Scopus)

抄録

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.

本文言語English
ホスト出版物のタイトルCollection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
ページ871-879
ページ数9
出版ステータスPublished - 2007 12 10
イベント43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference - Cincinnati, OH, United States
継続期間: 2007 7 82007 7 11

出版物シリーズ

名前Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
1

Conference

Conference43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
CountryUnited States
CityCincinnati, OH
Period07/7/807/7/11

ASJC Scopus subject areas

  • Space and Planetary Science

フィンガープリント 「Design study of turbine for pulse detonation combustor」の研究トピックを掘り下げます。これらがまとまってユニークなフィンガープリントを構成します。

引用スタイル