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http://dx.doi.org/10.6108/KSPE.2020.24.6.069

Performance Analysis of Liquid Pintle Thruster Using Quasi-one-dimensional Multi-phase Reaction Flow: Part I Key Sub-model Validation  

Kang, Jeongseok (Department of Aerospace and Mechanical Engineering, Korea Aerospace University)
Bok, Janghan (Department of Aerospace and Mechanical Engineering, Korea Aerospace University)
Sung, Hong-Gye (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
Kwon, Minchan (The 4th R&D Institute, Agency for Defense Development)
Heo, JunYoung (The 4th R&D Institute, Agency for Defense Development)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.24, no.6, 2020 , pp. 69-77 More about this Journal
Abstract
A quasi one-dimensional multi-phase reaction flow analysis code is developed for the performance analysis of liquid pintle thrusters. Unsteady flow field, droplet evaporation, finite reaction and film cooling models are composed as the major models of the performance analysis. The droplet vaporization takes account of Abramzon's vaporization model, and the combustion employs a flamelet model based on detail chemical reactions. Shine's model is applied for the film cooling calculation. To verify each model, the Sod shock tube, single droplet vaporization, kerosene droplets combustion, and film length are evaluated.
Keywords
Liquid Rocket Engine; Pintle Injector; Liquid Film; MultiPhase Reacting Flow;
Citations & Related Records
Times Cited By KSCI : 3  (Citation Analysis)
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