| ||Format||Pages||Price|| |
|PDF (696K)||18||$25||  ADD TO CART|
|Complete Source PDF (11M)||569||$69||  ADD TO CART|
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
Senior Research Engineer, Space Systems, Sacramento, CA
Senior Engineering Specialist, Space Systems, Sacramento, CA
Director, Space Systems, Sacramento, CA