| タイトル | Advanced rocket engine cryogenic turbopump bearing thermal model |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850018568 |
| 著者（英） | Cody, J. C.; Tiller, B. K.; New, L. S. |
| 著者所属（英） | Spectra Research Systems, Inc. |
| 発行日 | 1985-04-01 |
| 言語 | eng |
| 内容記述 | A lumped node thermal model was developed representing the Space Shuttle Main Engine (SSME) liquid oxygen (LOX) turbopump turbine end bearings operating in a cryogenically cooled bearing tester. Bearing elements, shaft, carrier, housing, cryogen flow characteristics, friction heat, and fluid viscous energy are included in the model. Heat transfer characteristics for the regimes of forced convection boiling are modeled for liquid oxygen (LOX) and liquid nitrogen (LN2). Large temperature differences between the cryogenic fluid and baring contact surfaces require detailed nodal representation in these areas. Internal loads and friction heat are affected by temperature dependent operating clearances requiring iterations between bearing thermal and mechanical models. Analyses indicate a thermal-mechanical coupling resulting in reduced operating clearances, increased loading and heating which can contribute to premature bearing failure. Contact surfaces operate at temperatures above local saturation resulting in vapor rather than liquid in the contacts, precluding possible liquid film lubrication. Elevated temperatures can reduce lubrication, increase friction, and reduce surface hardness supporting a surface failure mode rather than subsurface fatigue. |
| NASA分類 | MECHANICAL ENGINEERING |
| レポートNO | 85N26879 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/566966 |
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