Gas Generator Turbopump Power Calculator
Liquid rocket propulsion cycles: Calculate fuel and oxidizer pump hydraulic and shaft powers, required gas generator turbine drive flow, and cycle specific impulse penalty.
Fuel Pump Operating Conditions
e.g. RP-1, Methane, LH2
RP-1: 810, LCH4: 422, LH2: 71
1 MPa = 10 bar
Total pump efficiency
Oxidizer Pump Operating Conditions
e.g. Liquid Oxygen (LOX)
LOX: 1140 kg/m³
Inlet to discharge rise
Total pump efficiency
Turbine & Mechanical Transmission
Isentropic gas expansion work
Supersonic impulse/reaction stage
Shaft frictional and gear loss
Nominal chamber specific impulse
Turbopump Power Balance Output
Total Turbopump Shaft Power:
--
kW (Horsepower)
Required GG Turbine Flow:
--
kg/s (% of total engine flow)
Fuel Pump Shaft Power:
--
kW
Oxidizer Pump Shaft Power:
--
kW
| Total Engine Propellant Flow m_tot: | -- |
| Turbine Flow Fraction ζ_turb: | -- |
| Turbine Specific Work output W_turb: | -- |
| Engine Cycle Isp Penalty (Dump Loss): | -- |
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