The rocket redefined "massive," standing 363 feet (110 meters) in height and producing a ludicrous 7.68 million pounds (34 meganewtons) of thrust from the five monstrous, kerosene-gulping Rocketdyne F-1 rocket engines that made up its first stage.Īt the time, the F-1 was the largest and most powerful liquid-fueled engine ever constructed even today, its design remains unmatched (though see the sidebar, "The Soviets," for more information on engines that have rivaled the F-1). A closed-loop system with positive feedback associated with periodic oscillations mass flow rate of the propellant, and sudden heat release, was believed to account for the present combustion instability.There has never been anything like the Saturn V, the launch vehicle that powered the United States past the Soviet Union to a series of manned lunar landings in the late 1960s and early 1970s.
The pressure oscillations were enhanced by pulsated heat release. Therefore, a sudden release of heat occurred. Moreover, the mixing was highly enhanced when the pressure wave interacted with walls of the combustion chamber. The longitudinal pressure oscillations in the oxidizer post were found to be coupled with the transverse pressure waves in the combustion chamber and led to periodic oscillations of the mass flow rate of propellant. The driven regions of the combustion instability were identified on both sides of the combustion chamber through a Rayleigh index analysis. The numerical results for the frequency spectrum and spatial modes agree well with the theoretical analysis and experimental data. The physical mechanisms were systematically investigated through numerical simulations based on the stress-blended eddy simulation and flamelet-generated manifolds method with detailed chemical mechanisms (GRI Mech 3.0). Severe combustion instabilities occurred in the RMC during repeatable hot-fire tests. To better understand the combustion instability in methane/oxygen-fed rocket engines, the spontaneous transverse combustion instability in a rectangular multi-element combustor (RMC) was analyzed both experimentally and numerically.
A methane/oxygen mixture is considered to be an appropriate propellant for many future rocket engines due to its practicality and low cost.
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