Numerical Study and Performance Evaluation for Pulse Detonation Engine with Exhaust Nozzle 1st Report: Estimation on Performance Using a Detailed Reaction Model

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  • KIMURA Yuichiro
    青山学院大学大学院理工学研究科理工学専攻
  • TSUBOI Nobuyuki
    宇宙航空研究開発機構宇宙科学研究本部宇宙輸送工学研究系 現 九州工業大学大学院工学研究院機械知能工学研究系
  • HAYASHI A. Koichi
    青山学院大学理工学部機械創造工学科
  • YAMADA Eisuke
    青山学院大学理工学部機械創造工学科

Bibliographic Information

Other Title
  • 排気ノズルを有するパルスデトネーションエンジンの数値解析による推力性能評価　　第１報：詳細反応モデルによる基本性能の評価
  • ハイキ ノズル オ ユウスル パルスデトネーションエンジン ノ スウチ カイセキ ニ ヨル スイリョク セイノウ ヒョウカ ダイ1ポウ ショウサイ ハンノウ モデル ニ ヨル キホン セイノウ ノ ヒョウカ
  • Numerical Study and Performance Evaluation for Pulse Detonation Engine with Exhaust Nozzle
  • 1st Report: Estimation on Performance Using a Detailed Reaction Model
  • 第1報：詳細反応モデルによる基本性能の評価

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Abstract

This paper presents the propulsive performance evaluation for the H2/Air Pulse Detonation Engine (PDE) with a converging-diverging exhaust nozzle by the system-level modeling and multi-cycle numerical simulations. This study deals with the two-dimensional and axisymmetric compressible Euler equations with a detail chemical reaction model. First, single-shot propulsive performance of simplified-PDE, which is without exhaust nozzle, is evaluated to show the validity of the numerical and performance evaluation method. The influences of the initial conditions, ignition energy, grid resolution, and scale effects on the propulsive performance are studied with the multi-cycle simulations. The present results are compared with the results calculated by Ma et al. and Harris et al. and the difference between their results and the present simulations are approximately 2-3% because their chemical reactions use one-step model with one-γ model. The effects of the specific heat ratio should be estimated for various nozzle configurations and flight conditions.

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