I understand the basic principle of how a rocket engine works, but what I cannot find any info about is how do they initiate the whole process. Can someone please explain to me what gives the turbo-pump the initial "kick" to start the process of pumping the fuel and oxidizer?
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$\begingroup$ I think that startup methods are very specific to each rocket design. You may need to clarify which rocket, or else be prepared for very vague answers. Falcon 9 uses hypergolics, which are well suited to restarting in space. They need to purge the tanks or burn off the excess after landing the first stage as part of the process of rendering the booster safe to handle. As I recall, the SSME startup system was not capable of restarts. $\endgroup$– KengineerCommented Jun 16, 2016 at 21:21
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6$\begingroup$ This looks like a case where it is appropriate to list and briefly describe each option. It is an introductory question, that could provide an overview for someone just getting interested in space exploration, putting in one place information that is hard to find by googling or going to other introductory resources. $\endgroup$– kim holderCommented Jun 17, 2016 at 3:30
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1$\begingroup$ Possible duplicate of What limits the number of times that a liquid fueled rocket can restart? $\endgroup$– Russell BorogoveCommented Jun 17, 2016 at 4:26
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1$\begingroup$ @RussellBorogove: I'm not sure the dupe is actually similar enough; in particular, it seems to mostly concern restarts in flight, rather than starts on the ground, which is a distinction potentially worth exploring. $\endgroup$– Nathan TuggyCommented Jun 17, 2016 at 5:12
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1$\begingroup$ Actually, What are the phases of ignition (and flameout) of a liquid fuel engine? would make a better dupe :) Though my question concentrates more on chemistry and sequence of propellant mixing, and this one asks about technological details, the answer fits both. $\endgroup$– SF.Commented Jun 20, 2016 at 19:51
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2 Answers
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- Ariane 5: the Vulcain first stage engine is started using a small solid rocket motor.
- Shuttle SSME: after chilldown, the propellant valve is opened, allowing LH into the engine. This expands, driving the turbopump enough to fill the gas generators. The mixture in the gas generator is ignited and this drives the turbopump to operational speed.
When a start command is received, the MFV is immediately ramped to its full open position in two-thirds of a second (see Figure 9). This enables the LH2 to fill the downstream system and begin to power the high pressure turbines. The latent heat of the hardware imparts enough energy to the hydrogen to operate as an “expander-cycle” engine for the early part of the start sequence. This eliminates the need for any auxiliary power to initiate the start sequence,
- Saturn V F-1: The LOX valve opens, allowing LOX to flow through the turbopump, this starts it spinning. Some of the LOX flows to the gas generator. Then the propellant valve opens, RP-1 flows through the pump to the gas generator, the mixture in the gas generator is ignited and this drives the turbopump to operational speed. So basically this is gravity-fed until the gas generator ignites.
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6$\begingroup$ This answer totally needs the Soyuz story of 32 birch sticks: popularmechanics.com/space/rockets/a19966/… $\endgroup$– user54Commented Jun 21, 2016 at 5:09
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$\begingroup$ Thank you very much for your comment! I was particularly interested in Saturn V, so you made my day :) $\endgroup$ Commented Jul 4, 2016 at 6:25
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Often there is a starting extension to the gas generator. This extension contains a solid fuel which is ignited. The produced hot gas flows to the turbine and starts rotation. The turbine drives the turbo pumps for fuel and oxidizer. A small part of the fuel and oxidizer is pumped into the gas generator and ignited by the still burning solid fuel. The liquid fuel pumped into the gas generator continues the operation when the solid fuel burns out. The larger part of pumped fuel and oxidizer flows to the combustion chamber. When liquid oxygen and hydrogen or kerosene is used, a precise ignition inside the combustion chamber is necessary. A late ignition may cause a catastrophic destruction of the combustion chamber.
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$\begingroup$ Thank you very much for your comment! I appreciate you found time to answer my question. $\endgroup$ Commented Jul 4, 2016 at 6:26