A new design approach of a compact high performance bipropellant liquid rocket engine combustors

H. H. Chiu, T. L. Jiang

研究成果: Paper同行評審

2 引文 斯高帕斯(Scopus)

摘要

Based on the theory of group conjugate and normal combustion of bipropellants, a design procedure of a minimum length combustor for a prescribed combustion efficiency at fixed propellant flow rates and a constant fuel group combustion dumber is developed. Die optimum Sauter Mean Diameter (SMD) and the corresponding droplet number density that give the minimum burner length are provided to aid in the design of an optimum injector. It is estimated, for example, an approximately 10% reduction in a burner length la achieved when the SMD of oxidizer droplets is increased from 20 μm to 60 μm which is the optimum value for the selected flow rates- the minimum length requirement for the optimum burner is attributed to the rapid axial development of the combustion rate rather than the fast vaporization rate. The present approach can be used for all cryogenic propellants, partially cryogenic or non- cryogenic bipropellant combinations.

原文English
出版狀態Published - 1987
事件AIAA/ASME/SAE/ASEE 23rd Joint Propulsion Conference, 1987 - San Diego, United States
持續時間: 1987 六月 291987 七月 2

Other

OtherAIAA/ASME/SAE/ASEE 23rd Joint Propulsion Conference, 1987
國家/地區United States
城市San Diego
期間87-06-2987-07-02

All Science Journal Classification (ASJC) codes

  • 機械工業
  • 航空工程
  • 能源工程與電力技術
  • 控制與系統工程
  • 電氣與電子工程

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