| タイトル | Cooling of High Pressure Rocket Thrust Chambers with Liquid Oxygen |
| 本文（外部サイト） | http://hdl.handle.net/2060/19800014876 |
| 著者（英） | Price, H. G. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1980-01-01 |
| 言語 | eng |
| 内容記述 | An experimental program using hydrogen and oxygen as the propellants and supercritical liquid oxygen (LOX) as the coolant was conducted at 4.14 and 8.274 MN/square meters (600 and 1200 psia) chamber pressure. Data on the following are presented: the effect of LOX leaking into the combustion region through small cracks in the chamber wall; and verification of the supercritical oxygen heat transfer correlation developed from heated tube experiments; A total of four thrust chambers with throat diameters of 0.066 m were tested. Of these, three were cyclically tested to 4.14 MN/square meters (600 psia) chamber pressure until a crack developed. One had 23 additional hot cycles accumulated with no apparent metal burning or distress. The fourth chamber was operated at 8.274 MN/square meters (1200 psia) pressure to obtain steady state heat transfer data. Wall temperature measurements confirmed the heat transfer correlation. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 80N23365
NASA-TM-81503
E-441 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/172606 |
