![]() ![]() Typically, propellant flows through two kinds of combustion chambers the first called preburner and the second called main combustion chamber. ![]() The main advantage relative to other rocket engine power cycles is high fuel efficiency, measured through specific impulse, while its main disadvantage is engineering complexity. In the staged combustion cycle, propellant flows through multiple combustion chambers, and is thus combusted in stages. The staged combustion cycle (sometimes known as topping cycle, preburner cycle, or closed cycle) is a power cycle of a bipropellant rocket engine. After being run through a turbine to power the pumps, the gas is injected into the combustion chamber and burned with the remaining oxidizer. Here, all of the fuel and a portion of the oxidizer are fed through the preburner, generating fuel-rich gas.
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