| タイトル | Research for advanced turbine cooling technology |
| その他のタイトル | Research for advanced turbine cooling technology |
| 著者（日） | 仲俣 千由紀; 筑後 一義; 松野 伸介 |
| 著者（英） | Nakamata, Chiyuki; Chikugo, Kazuyoshi; Matsuno, Shinsuke |
| 著者所属（日） | 石川島播磨重工業 航空宇宙事業本部 技術開発センター; 石川島播磨重工業 技術開発本部 基盤技術研究所; 石川島播磨重工業 技術開発本部 基盤技術研究所 |
| 著者所属（英） | Ishikawajima-Harima Heavy Industries Co. Ltd. Research and Engineering Division, Aero-Engine and Space Operations; Ishikawajima-Harima Heavy Industries Co. Ltd. Research Laboratory, Research & Development; Ishikawajima-Harima Heavy Industries Co. Ltd. Research Laboratory, Research & Development |
| 発行日 | 2005-08-01 |
| 刊行物名 | IHI Engineering Review
IHI Engineering Review |
| 巻 | 38 |
| 号 | 2 |
| 開始ページ | 63 |
| 終了ページ | 69 |
| 刊行年月日 | 2005-08-01 |
| 言語 | eng |
| 抄録 | Environmentally compatible supersonic propulsion systems require methods to effectively cool the hot components like turbines with minimum coolant. A new transpiration structure concept was developed and its advantages in cooling performance, fracture toughness, and manufacturability were verified in the ESPR (Research and Development of Environmentally Compatible Propulsion System for Next Generation Supersonic Transport) project. Another issue relevant to the advanced cooling research in the project was highly accurate prediction of component temperatures. A newly developed conjugate analysis method was validated with the engine data and the turbine rim ingress mechanism was clarified with rig test and CFD (Computational Fluid Dynamics). |
| キーワード | supersonic aircraft; supersonic turbine; internal cooling system; transpiration cooling; computational fluid dynamics; fracture strength; temperature distribution; 超音速航空機; 超音速タービン; 内部冷却系; 吹き出し冷却; 計算流体力学; 破壊強度; 温度分布 |
| 資料種別 | Journal Article |
| ISSN | 0018-9820 |
| SHI-NO | AA0048286003 |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/30328 |
