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The liquid rocket engine turbopump is a unique piece of rotating machinery, its tipically pumping cryogenic liquids, which usually consist of LOX (Liquid oxigen), while being driven by high temperature gases, posing large temperature differentials between pump and turbine. The pump muyst avoid cavitation, while pumping relatively high-density fluids at low inlet pressures, and deliver them to the thrust chamber at very high pressures over a relatively wide throtting range.
The different chambers of the turbopump need to be sealed at their mating points in a static face seal configuration known as inter-propellant seals. IPS is simply a series of cascading regular seals trying to eliminate bleed-through around the rotating components of the turbopump and they need on both the fuel pump and turbine sides. Through thermal models in ANSYS, it is determined that the sealing surfaces on both sides of the turbo pump can reach temperatures as low as -300 F on the pump section and as high as 700F on the turbine section. METCAR´s M-444 & M-45 carbon grades are being used as sealing material on both sections.
M-444
M-45
Contact us for more information:
T. +914 941 3778 / sales@metcar.com
