Abstract
The role of the injector is atomization and mixing. It dictates the size and geometry of the combustion chamber and gas generator. Experiments are conducted with water-cooled adjustable length gas generator for a liquid rocket engine with two types of injectors at a lower mixing ratio. Tests are conducted at characteristic length of 1.75 and 4.27 m. Liquid oxygen and kerosene are used as propellants. Single pressure swirl coaxial injector and three like doublet impinging injectors are used. Combustion performance is studied and compared on the base of characteristic velocity. Characteristic velocity is found high at short length but is found low at larger length for pressure swirl injector as compare to impinging injectors.
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