マイクロスケール超音速軸流圧縮機の空力性能予測モデル

カテゴリ: 論文誌(論文単位)

グループ名: 【E】センサ・マイクロマシン部門

発行日: 2024/08/01

タイトル(英語): Aerodynamic Performance Prediction Model for Microscale Supersonic Axial Compressor

著者名: 糸井　正隆（立命館大学 理工学部），舟田　晋（立命館大学 理工学部），鈴木　隼人（立命館大学 理工学部），石黒　聡（立命館大学 理工学部），原田　拓実（立命館大学 理工学部），鳥山　寿之（立命館大学 理工学部）

著者名(英語): Masataka Itoi (College of Science and Engineering, Ritsumeikan University), Susumu Funada (College of Science and Engineering, Ritsumeikan University), Hayato Suzuki (College of Science and Engineering, Ritsumeikan University), Satoshi Ishiguro (College of Science and Engineering, Ritsumeikan University), Takumi Harada (College of Science and Engineering, Ritsumeikan University), Toshiyuki Toriyama (College of Science and Engineering, Ritsumeikan University)

キーワード: マイクロスケール超音速軸流圧縮機，圧縮機空力性能，保存則，レイノルズ輸送定理　　micro-scale supersonic axial compressor，compressor aerodynamic performance，conservation laws，Reynolds transport theorem

要約(英語): A supersonic one-dimensional flow model for a microscale supersonic axial compressor was derived by applying the conservation laws of mass flow rate, momentum, and energy and the Reynolds transport theorem. For the convenience of early-stage aerodynamic design, we proposed a compressor performance map that shows the correlation between blade geometry, flow path geometry, and aerodynamic performance. As a result, we clarified the effects of changes in the positive and negative blade camber angles and expansion and contraction of the meridian flow path area on the total pressure ratio and adiabatic efficiency using a straight blade as a reference.

本誌: 電気学会論文誌E（センサ・マイクロマシン部門誌） Vol.144 No.8 （2024）

本誌掲載ページ: 206-218 p

原稿種別: 論文／日本語

電子版へのリンク: https://www.jstage.jst.go.jp/article/ieejsmas/144/8/144_206/_article/-char/ja/