SEDL / STP / STP1111-EB / STP17787S

Test Experience with a High-Pressure Oxygen Turbopump and Heat Exchanger

Schoenman, L
Senior Research Engineer, Space Systems, Sacramento, CA

Sabiers, RL
Senior Engineering Specialist, Space Systems, Sacramento, CA

McIlwain, MC
Director, Space Systems, Sacramento, CA

Pages: 18    Published: Jan 1991

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Abstract

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.