| タイトル | Experimental Determination of the Dynamic Hydraulic Transfer Function for the J-2X Oxidizer Turbopump |
| 本文（外部サイト） | http://hdl.handle.net/2060/20120002801 |
| 著者（英） | Patel, Sandeep; Zoladz, Tom; Karon, Dave; Lee, Erik |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2011-12-05 |
| 言語 | eng |
| 内容記述 | An advanced methodology for extracting the hydraulic dynamic pump transfer matrix (Yp) for a cavitating liquid rocket engine turbopump inducer+impeller has been developed. The transfer function is required for integrated vehicle pogo stability analysis as well as optimization of local inducer pumping stability. Laboratory pulsed subscale waterflow test of the J-2X oxygen turbo pump is introduced and our new extraction method applied to the data collected. From accurate measures of pump inlet and discharge perturbational mass flows and pressures, and one-dimensional flow models that represents complete waterflow loop physics, we are able to derive Yp and hence extract the characteristic pump parameters: compliance, pump gain, impedance, mass flow gain. Detailed modeling is necessary to accurately translate instrument plane measurements to the pump inlet and discharge and extract Yp. We present the MSFC Dynamic Lump Parameter Fluid Model Framework and describe critical dynamic component details. We report on fit minimization techniques, cost (fitness) function derivation, and resulting model fits to our experimental data are presented. Comparisons are made to alternate techniques for spatially translating measurement stations to actual pump inlet and discharge. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | M11-0639 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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