Orbital Transfer Vehicle Oxygen Turbopump Technology. Final Report, Volume 2.Nitrogen and Ambient Oxygen Testing
Abstract
This report covers the testing of a rocket engine oxygen turbopump (TPA) using high pressure ambient temperature nitrogen and oxygen as the turbine drive gas in separate test series. The pumped fluid was liquid nitrogen or liquid oxygen. The TPA is designed to operate with 400 F oxygen turbine drive gas. Following bearing tests, the TPA was finish machined (impeller blading and inlet/outlet ports). The hydrostatic bearing system requires a bearing pressurization system. Two test series were successfully completed with the bearing assist supplied only by the pump second stage output which entailed a rubbing start until pump pressure builds up. The final test series used ambient oxygen drive and no external bearing assist. Total operating time was 2268 seconds. There were 14 starts without bearing assist and operating speeds up 80, 000 rpm were logged. Teardown examination showed some smearing of silverplated bearing surfaces but no exposure of the underlying monel material. There was no evidence of melting or oxidation due to the oxygen exposure. The articulating, self-centering hydrostatic bearing exhibited no bearing load or stability problems. The only anomaly was higher than predicted flow losses which were attributed to a faulty ring seal. The TPA will be refurbished prior to the 400 F oxygen test series but its condition is acceptable, as is , for continued operating.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1990
- Accession Number
- ADA234757
Entities
People
- B. H. Chen
- P. S. Buckmann
- R. J. Brannam
- R. L. Sabiers
- S. J. Church
Organizations
- Aerojet Rocketdyne Holdings