No abstract

Vapor-water two phase flow separation in pressure vessel of nuclear power plants is accomplished with swirl motion using vanes. In order to reduce separation pressure loss and to make it economic, a new type of low cost simplified innovative separator using lattice core configuration is proposed where swirling is caused by the orthogonal driving flow. The performance of the separator has been assessed numerically with the commercial CFD code FLUENT 14.0. The numerical analysis is compared with the experiment. The geometry and flow conditions are chosen according to the experiment. In the analysis, standard k – e and realizable k – e turbulence models are implemented. The prediction of maximum air void fraction with realizable k – e model was almost the same as input air void fraction but the void fraction computed by standard k – e model was compared better with the experimental results than the realizable k – e model. Some discrepancies in flow pattern between the experimental and simulation results are observed which might be due to the difference of nozzle shape. However, a more detailed model is necessary to arrive at the final conclusion.

This study is an investigation of fuel regression characteristics in an axial-injection endburning hybrid rocket using nitrous oxide. Experiments were conducted using ϕ 38 mm cylindrical fuel grains with an array of 0.8 mm ports made from curable. Previous studies of end-burning hybrid rockets used gaseous oxygen as the oxidizer. Nitrous oxide may be more suitable than the gaseous oxygen for use in space-based missions because of the weight savings associated with the oxidizer storage vessels, supply system, and motor mass. In this study, two types of nozzle closures were employed to increase the initial chamber pressure and promote

No abstract

This study is an investigation of fuel regression characteristics in an axial-injection endburning hybrid rocket using nitrous oxide. Experiments were conducted using ϕ 38 mm cylindrical fuel grains with an array of 0.8 mm ports made from curable. Previous studies of end-burning hybrid rockets used gaseous oxygen as the oxidizer. Nitrous oxide may be more suitable than the gaseous oxygen for use in space-based missions because of the weight savings associated with the oxidizer storage vessels, supply system, and motor mass. In this study, two types of nozzle closures were employed to increase the initial chamber pressure and promote