Concepts NREC, LLC — Department of Defense SBIR Phase I: AF181-031

Description

A novel integrated inter-propellant seal and thrust bearing (IPS/TB) for rocket turbopump applications that uses the latest technology developments in seal coatings and additive manufacturing to advance the state-of-the-art. The IPS/TB has low propellant loss, requires little or no purge gas, and no continuous purge when the turbopump is not in operation. The thrust bearing portion can handle all the turbopump thrust requirements for an upper-stage or in space propulsion engine in a simple package without the axial stack-up tolerance problems or secondary flow losses associated with other thrust management solutions. The technology is applicable to turbopumps for booster, upper-stage, and in-space propulsion engines and for a variety of propellants including, LOX, LH2, LNG, and RP1.