Working temperature is the pump turbine operating temperature. A higher working temperature generally gives a higher power and a lower reliability. The working temperature is limited by the melting points of the materials used, unless they use the liquids for cooling, as when spinning the rocket engines around a pivot and pressurizing the reactants with centrifugal force.

An evaporation turbine will usually operate at about seven hundred degrees Kelvin. A hot gas turbine, like the one powering the space shuttle main engine turbopumps, will operate at fifteen hundred degrees Kelvin. Spinning the rocket engines around a pivot and pressurizing the reactants with centrifugal force, can be viewed as a pump operating at combustion temperature. Working temperature is used along with propellant usage and pump efficiency to calculate the propellant energy which is in turn used to calculate the pump boost.

propellant energy = propellant usage * pump efficiency * working temperature * 8,314 J * K / kmol / 0.2
 

combustion exhaust = combustion ratio / exhaust molecular

uncombustion = 1.0 - combustion ratio

pump energy = propellant energy * propellant mass ratio / propellant molecular + propellant energy * reactant propellant usage * ( fuel mass ratio * ( uncombustion / fuel molecular + combustion exhaust ) + oxidizer mass ratio * ( uncombustion / oxidizer molecular + combustion exhaust ) )

pump boost = pump energy / pump need
pump power = pump energy * fuel flow
 
 

This is used in astropolis, pumped rocket and rocket cost.
 
 

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