The to visualize and analyze the flow and

The
principal aim is to describe and discuss the mixing and burning of propellants in large liquid rocket engine under supercritical condition
where the distinction between liquid and gas phase would be incomprehensible.
Most of the studies focused on transition behavior, at the moment of ignition,
temperature and pressure increase drastically therefore thermodynamic and fluid
dynamic properties of liquid and gas phase coexist. Ignition process is divided
in four phases;(i) primary ignition (ii) flame lift-off (iii) flame propagation
(iv) flame anchoring. During ignition, transient mixing phenomena are described.
The different processes are identified by different experimental approaches. The
ignition transition of GOx/Kerosene spray was observed by shadowgraph technique.
Cryogenic fluids were injected into various gaseous under both cold flow and
hot fire conditions. The discussion begins with hot fire investigation of
Lox/GH2 injection under sub and super critical conditions in windowed
combustion chamber. At the critical point, which is characterized by the
critical temperature and pressure, the density of the gas and liquid phase
become the same. Shadow photography has been used as a diagnostic method to
visualize the oxygen and hydrogen. The computational fluid dynamics (CFD) code
Aero shape 3D was utilized. Steady state mass flow rate of GOx/Kerosene was
calculated with the help of oxidizer. Orifices were inserted to prevent reverse
flow at the moment of ignition. The
aim of this study is to visualize and analyze the flow and flame transients
during engine ignition. The effects of
ignition timing and time responses of injection and combustion pressure at the
moment of ignition were investigated. The crest pressure at the moment of
ignition caused the immediate discontinuance of propellant injection. The
ignition transient of GOx/kerosene spray was successfully observed. Experimental and computational results were
compared.