| タイトル | Analysis of a Cylindrical Specimen Heated by an Impinging Hot Hydrogen Jet |
| 本文（外部サイト） | http://hdl.handle.net/2060/20060026040 |
| 著者（英） | Luong, Van; Litchford, Ron; Chen, Yen-Sen; Foote, John; Wang, Ten-See |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2006-01-01
2006 |
| 言語 | eng |
| 内容記述 | A computational conjugate heat transfer methodology was developed, as a first step towards an efficient and accurate multiphysics, thermo-fluid computational methodology to predict environments for hypothetical solid-core, nuclear thermal engine thrust chamber and components. A solid conduction heat transfer procedure was implemented onto a pressure-based, multidimensional, finite-volume, turbulent, chemically reacting, thermally radiating, and unstructured grid computational fluid dynamics formulation. The conjugate heat transfer of a cylindrical material specimen heated by an impinging hot hydrogen jet inside an enclosed test fixture was simulated and analyzed. The solid conduction heat transfer procedure was anchored with a standard solid heat transfer code. Transient analyses were then performed with ,variable thermal conductivities representing three composites of a material utilized as flow element in a legacy engine test. It was found that material thermal conductivity strongly influences the transient heat conduction characteristics. In addition, it was observed that high thermal gradient occur inside the cylindrical specimen during an impulsive or a 10 s ramp start sequence, but not during steady-state operations. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | AIAA Paper 2006-2926 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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