Turbopump Impeller Tip Leakage Calculator
Rocket turbomachinery clearances: Model annular shroud and wear-ring seal leakage flow rates, volumetric efficiency losses, and parasitic hydraulic power dissipation.
Impeller & Seal Geometry
Seal contact diameter
Typical: 100–300 μm
Axial land engagement length
Frictional resistance configuration
Operating Hydrodynamic Conditions
Discharge to eye pressure difference
LOX: 1140, RP-1: 810, LH2: 71
Useful delivery flow rate
Internal overall efficiency
Leakage Flow & Volumetric Loss Output
Leakage Mass Flow Rate:
--
kg/s (recirculated)
Volumetric Efficiency η_vol:
--
% useful delivered flow
Parasitic Hydraulic Power Loss:
--
kW shaft power dissipated
Annular Clearance Area A_c:
--
mm²
| Discharge Coefficient C_d: | -- |
| Jet Leakage Velocity V_leak: | -- |
| Volumetric Leakage Flow Q_leak: | -- |
| Leakage Fraction of Main Flow: | -- |
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