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  • 1
    facet.materialart.
    Unknown
    Bearing tester data compilation, analysis and reporting and bearing math modeling, volume 1 (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Thermal and mechanical models of high speed angular contact ball bearings operating in LOX and LN2 were developed and verified with limited test data in an effort to further understand the parameters that determine or effect the SSME turbopump bearing operational characteristics and service life. The SHABERTH bearing analysis program which was adapted to evaluate shaft bearing systems in cryogenics is not capable of accommodating varying thermal properties and two phase flow. A bearing model with this capability was developed using the SINDA thermal analyzer. Iteration between the SHABERTH and the SINDA models enable the establishment of preliminary bounds for stable operation in LN2. These limits were established in terms of fluid flow, fluid inlet temperature, and axial load for a shaft speed of 30,000 RPM.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-171039 , NAS 1.26:171039 , SRS/SE-TR84-022-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Assessment of the operating characteristics of the SSME LOX turbopump pump-end bearing (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A bearing/shaft model of the SSME LOX turbopump was developed using the SHABERTH bearing/shaft math modeling computer code. A previously developed bearing/shaft thermal model of the SSME LOX turbopump turbine and bearing was used in conjunction with SHABERTH to evaluate the thermomechanical operating characteristics of the LOX turbopump end bearings. Results show that for the two unmounted diametrical clearances evaluated (4.0 mils and 6.3 mils), the inboard pump end bearing supports about 81% of the isolator load for the small clearance and 77% of the isolator load for the larger clearance. Bearing clearance changes due to thermal effects were 40% for the 4.0 mil diametrical clearance case and 19% for the 6.3 mil clearance case evaluated. The thermal analysis included evaluation of bearing temperatures for a subcooled case and a saturated case. Results indicate that no drastic temperature change occurred between the two cases. Since the rolling element and race surfaces of the subcooled case were at temperatures sufficiently high enough to be vapor blanketed, exceeding saturation temperature at the bearing inlet did not increase surface temperatures greatly.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-171287 , NAS 1.26:171287 , SRS/STD-TR85-009
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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