Senior Research Engineer, Space Systems, Sacramento, CA
Senior Engineering Specialist, Space Systems, Sacramento, CA
Director, Space Systems, Sacramento, CA
Pages: 18 Published: Jan 1991
Test results of a 97 KW (130 hp) Monel turbopump assembly driven by 300 K (540 R), 27.6 MPa (4000 psi) oxygen at a speed of 62,000 rpm while supported on oxygen-pressurized hydrostatic bearings is presented, along with test results for a 27.6 MPa (4000 psi), 644 K (1159 R) oxygen/hydrogen heat exchanger. These new rocket components incorporate design and material selection criteria which have evolved from NASA and ASTM G-4 standards and test methods. Both components employ alloys that have low heats of combustion and high thermal diffusivity as a means of meeting a self-extinguishing safety criteria.
metal ignition, oxygen turbopump, oxygen heat exchanger, oxygen compatibility, nickel and copper alloys
Paper ID: STP17787S