SYMPOSIA PAPER Published: 01 January 1991

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


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.

Author Information

Schoenman, L
Space Systems, Sacramento, CA
Sabiers, RL
Space Systems, Sacramento, CA
McIlwain, MC
Space Systems, Sacramento, CA
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Developed by Committee: G04
Pages: 556–573
DOI: 10.1520/STP17787S
ISBN-EB: 978-0-8031-5170-3
ISBN-13: 978-0-8031-1461-6