Staged combustion cycle (rocket) | Wikipedia audio article
Channel: wikipedia tts
Date: 2019-05-17

This is an audio version of the Wikipedia Article:
https://en.wikipedia.org/wiki/Staged_combustion_cycle


00:01:11 1 History
00:03:34 2 Variants
00:05:06 2.1 Full-flow staged combustion cycle
00:06:52 3 Applications
00:07:00 3.1 Oxidizer-rich staged combustion
00:09:05 3.2 Fuel-rich staged combustion
00:09:56 3.3 Full-flow staged combustion
00:10:34 3.4 Current/past applications of staged-combustion engines
00:10:45 3.5 Future applications of staged-combustion engines
00:11:02 4 See also



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SUMMARY
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The staged combustion cycle (sometimes known as topping cycle or preburner cycle) is a power cycle of a bipropellant rocket engine. In the staged combustion cycle, propellant flows through multiple combustion chambers, and is thus combusted in stages. 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.
Typically, propellant flows through two kinds of combustion chambers; the first called preburner and the second called main combustion chamber. In the preburner, a small portion of propellant is combusted, and the over-pressure produced is used to drive the turbopumps that feed the engine with propellant. In the main combustion chamber, the propellants are combusted completely to produce thrust.
The fuel efficiency of the staged combustion cycle is in part a result of all propellant ultimately flowing to the main combustion chamber; contributing to thrust. The staged combustion cycle is sometimes referred to as closed cycle, as opposed to the gas generator, or open cycle where a portion of propellant never reaches the main combustion chamber. The engineering complexity is partly a result of the preburner exhaust of hot and highly pressurized gas which, particularly when oxidizer-rich, produces extremely harsh conditions for turbines and plumbing.