Droplet size and velocity measurements in a cryogenic jet flame of a rocket-type combustor using high speed imaging [PDF]
Atomization and Sprays, Volume 26, Issue 5, 2016, pp. 411-438Injectors of cryogenic liquid rocket engines produce large polydisperse and dense sprays due to the pressure and mass flow conditions. Atomization is the dominating process that drives the flame behaviour in cryogenic jet flames, when the propellants are injected in subcritical conditions.
arxiv +1 more source
Reduced Order Modeling Framework for Combustor Instabilities Using Truncated Domain Training [PDF]
, 2018 A multi-fidelity framework is established and demonstrated for prediction of combustion instabilities in rocket engines. The major idea is to adapt appropriate fidelity modeling approaches for different components in a rocket engine to ensure accurate and efficient predictions.
arxiv +1 more source
, 2015 Effects of injection conditions on a pintle injector which is proper to recent liquid rocket engines requiring low cost, low weight, high efficiency and reusability were studied.
Min Son +4 more
semanticscholar +1 more source
Application of a double-dead-time model describing chugging to liquid propellant rocket engines having multielement injectors [PDF]
Double-dead-time model describing chugging to liquid propellant rocket engines having multielement ...
Szuch, J. R.
core +1 more source
A study of high frequency nonlinear combustion instability in baffled annular liquid propellant rocket motors. Volume 2 - A user manual for computer programs TRDL and TRDPLT Final report, 25 Aug. 1969 - 25 Sep. 1970 [PDF]
User manual for computer programs to determine high frequency instability in baffled annular liquid propellant rocket engines - Vol.
Burstein, S. Z., Schechter, H. S.
core +1 more source
Atomization and dense-fluid breakup regimes in liquid rocket engines
, 2015 Until recently, modern theory has lacked a fundamentally based model to predict the operating pressures where classical sprays transition to dense-fluid mixing with diminished surface tension.
R. Dahms, J. Oefelein
semanticscholar +1 more source
LOX/Hydrogen Coaxial Injector Atomization Test Program [PDF]
Quantitative information about the atomization of injector sprays is needed to improve the accuracy of computational models that predict the performance and stability margin of liquid propellant rocket engines.
Zaller, M.
core +1 more source
Low loss injector for liquid propellant rocket engines [PDF]
, 1986 A low pressure loss injector element is disclosed for the main combustion chamber of a rocket engine which includes a lox post terminating in a cylindrical barrel. Received within the barrel is a lox plug which is threaded in the lox post and includes an
Vonpragenau, G. L.
core +1 more source
Model Rocket Project for Aerospace Engineering Course: Trajectory Simulation and Propellant Analysis [PDF]
arXiv, 2017 Model rockets have been employed in student projects, but very few papers in aerospace education offer concise summaries of activities at university-course levels. This paper aims to address this gap in the literature. The rockets used by our students reached some 500 m (~1,640 feet) in altitude, deployed a parachute, and spent 2-3 minutes descending ...
arxiv
A numerical model to predict unsteady cavitating flow behaviour in inducer blade cascades [PDF]
arXiv, 2020 The cavitation behaviour of a four-blade rocket engine turbopump inducer is simulated. A 2D numerical model of unsteady cavitation was applied to a blade cascade drawn fromthe inducer geometry. The physical model is based on a homogeneous approach of cavitation, coupled with a barotropic state law for the liquid/vapour mixture.
arxiv