| タイトル | Oil cooling system for a gas turbine engine |
| 本文（外部サイト） | http://hdl.handle.net/2060/19780002524 |
| 著者（英） | Kast, H. B.; Coffinberry, G. A. |
| 著者所属（英） | General Electric Co.|NASA Lewis Research Center |
| 発行日 | 1977-08-16 |
| 言語 | eng |
| 内容記述 | A gas turbine engine fuel delivery and control system is provided with means to recirculate all fuel in excess of fuel control requirements back to aircraft fuel tank, thereby increasing the fuel pump heat sink and decreasing the pump temperature rise without the addition of valving other than that normally employed. A fuel/oil heat exchanger and associated circuitry is provided to maintain the hot engine oil in heat exchange relationship with the cool engine fuel. Where anti-icing of the fuel filter is required, means are provided to maintain the fuel temperature entering the filter at or above a minimum level to prevent freezing thereof. Fluid circuitry is provided to route hot engine oil through a plurality of heat exchangers disposed within the system to provide for selective cooling of the oil. |
| NASA分類 | MECHANICAL ENGINEERING |
| レポートNO | 78N10467 |
| 権利 | No Copyright |
