並列タイトル等Development of the Highly Loaded Axial Flow Turbine Airfoils, Making Use of the Improved Inverse Channel Flow Design Method
タイトル（掲載誌）航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-5
一般注記To reduce the number of the turbine airfoils or the solidity as far as possible without increasing energy loss, a study of highly loaded turbine airfoils has been conducted. These new airfoils were designed for the typical velocity diagrams of the first and second stages of a jet engine low pressure turbine. With regard to the design procedures, an improved inverse method, and also a boundary layer analysis technique were employed to optimize the airfoil shapes. These newly developed airfoils, and state-of-the-art aft loaded conventional airfoils designed for almost equivalent velocity diagrams were tested in the high speed cascade wind tunnel. These new airfoils showed lower kinetic energy loss coefficient characteristics and wider useful incidence ranges over the wider range extended to the high subsonic regime compared with the aft loaded ones, in spite of their higher loading. In addition to some main parts of the design procedures, theoretical nd experimental results are discussed.
資料番号: NALSP0005011
レポート番号: NAL SP-5
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=43191&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ