| タイトル | Preliminary Evaluation of a Turbine/Rotary Combustion Compound Engine for a Subsonic Transport |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760014112 |
| 著者（英） | Civinskas, K. C.; Kraft, G. A. |
| 著者所属（英） | NASA Lewis Research Center|Army Air Mobility Research and Development Lab. |
| 発行日 | 1976-03-01 |
| 言語 | eng |
| 内容記述 | The fuel consumption of a modern compound engine with that of an advanced high pressure ratio turbofan was compared. The compound engine was derived from a turbofan engine by replacing the combustor with a rotary combustion (RC) engine. A number of boost pressure ratios and compression ratios were examined. Cooling of the RC engine was accomplished by heat exchanging to the fan duct. Performance was estimated with an Otto-cycle for two levels of energy lost to cooling. The effects of added complexity on cost and maintainability were not examined and the comparison was solely in terms of cruise performance and weight. Assuming a 25 percent Otto-cycle cooling loss (representative of current experience), the best compound engine gave a 1.2 percent improvement in cruise. Engine weight increased by 23 percent. For a 10 percent Otto-cycle cooling loss (representing advanced insulation/high temperature materials technology), a compound engine with a boost PR of 10 and a compression ratio of 10 gave an 8.1 percent lower cruise than the reference turbofan. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 76N21200
NASA-TM-X-71906
E-8695 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/186417 |
