Dynamic Response Analysis of High-Pressure Rocket Pumps

スポンサーリンク

概要

• 論文の詳細を見る

• With regard to the development of a liquid-fuel rocket engine, knowledge of unsteady characteristics of turbopumps is essential in attempts to increase rocket reliability. Numerical simulation is very advantageous in determining the unsteady characteristics of turbopumps, and knowledge thus obtained can contribute to decreasing the cost and the number of experiments. In the present study, the effect of compressibility of cryogenic propellants, such as liquid hydrogen (LH2) and liquid oxygen (LOX), and the effect of nonlinearity of flow on the dynamic response of a high-pressure turbopump were considered. The results of calculation were compared with a nonlinear incompressible mathematical model. The effects of dynamic characteristics of a cavitating inducer, such as cavitation compliance and mass flow gain factor, as well as the effect of pipe elasticity and that of an accumulator for the POGO suppressor, were also analyzed.

• 社団法人 日本航空宇宙学会の論文
• 2004-11-04

著者

• Jun Sang-in

  Graduate School Of Engineering Tohoku University

• TOKUMASU Takashi

  Institute of Fluid Science, Tohoku University

• KAMIJO Kenjiro

  Institute of Fluid Science, Tohoku University

• Kamijo Kenjiro

  Institute Of Fluid Science Tohoku University

• Tokumasu Takashi

  Institute Of Fluid Science Tohoku University

関連論文

• Dynamic Response Analysis of High-Pressure Rocket Pumps
• Two-Dimensional Numerical Simulation of Boiling Two-Phase Flow of Liquid Nitrogen
• Two-Dimensional Numerical Analysis of Boiling Two-Phase Flow of Liquid Helium
• The Structure of Free Jet Expansion of Binary Gas Mixture
• Thermal conductivity of diatomic liquid in a narrow channel including a nanobubble
• The Numerical Analysis of the Effect of Flow Properties on the Thermodynamic Effect of Cavitation
• Large-scale Molecular Dynamics Simulations for Analyses of Transport Phenomena in Polymer Electrolyte Fuel Cell

スポンサーリンク