2019年2月5日 · First, all of the propellants are burned in the preburners, thus providing more mass flow for turbine drive power than the conventional staged combustion cycle. This additional power can be used to increase the chamber pressure and produce a smaller engine; alternatively, the preburner temperature can be reduced to provide the same power at ...

It shows an analysis that concludes for equal turbine temperatures and pump discharge pressures, an oxidizer-rich cycle has an 87% increase in chamber pressure over a fuel-rich cycle. This would seem to imply that a smaller oxidizer-rich engine could produce the same thrust as a larger fuel-rich engine.

2017年9月9日 · My idea is to do a hybrid between staged combustion and FFSC. By this I mean having two preburners to get the benefits of FFSC, but running them both fuel rich for simplicity. So it would essentially be a fuel rich staged combustion cycle, but with two separate preburners/turbopumps to eliminate the shaft seal, lighter weight, etc. Good idea ...

2016年10月7日 · For a Full FLow Staged Combustion Cycle engine there are two combustion chambers driving two turbines; one to drive the fuel pump, and the other to drive the oxidizer pump. This "two shaft" solution solves problems that …

2017年4月5日 · Yes. Full Flow Staged Combustion is both a Fuel Rich and Oxidizer Rich Staged Combustion combined together so both parts all go through partial combustion first and then a final combustion later. Your left drawing would be Fuel Rich staged combustion where all of the fuel goes through partial combustion but the Oxidizer is just pumped in.

2020年2月1日 · Part of that reliability is from it being an expander though--the fewer combustion devices you have, the better. GG's are often used as upper stage engines too though--SpaceX M1vac and J-2X. I also believe that SpaceX's Starship upper stage will also be powered by staged combustion Raptors.

2024年8月16日 · "A quick search tells me that: hydrazine monopropellant 222-230 vac isp; nitrous oxide monopropellant 80-140 vac isp; hypergolic gas generator (Viking) 281-301 vac isp; hypergolic oxidizer rich staged combustion (Proton) 316 vac isp; hypergolic full flow staged combustion (RD-270) 322 seconds vacuum. I could not find info on nitrogen tetroxide ...

At first, I thought having two pre-combustion chambers and two turbo pumps would double the power compared to an RD-180 style oxygen-rich-only staged combustion engine. But then I did this calculation (see below) of fuel mass and concluded that the fuel has only 25% of the mass of the oxygen, and so would only add 25% to the total pump power ...

2020年2月2日 · To set the context, here is my understanding of the expander cycle: Closed expander cycle is very efficient, perhaps more efficient than staged combustion cycle. It also has very little mechanical complexity as compared to other cycles (look at the simplicity of BE-7) which makes it very reliable (look at the longevity of RL-10). But closed ...

2023年10月10日 · As a result, chemical rocket combustion chambers are designed to run fuel- or oxidizer-rich for durability reasons. Either fuel- or oxidizer-rich conditions will lower combustion temperature, but fuel-rich has the added advantage of lower exhaust gas molecular weight and therefore higher exhaust velocity ( Isp).