数値計算による複合エンジンの静止大気中における吸い込み性能予測

• Material Type: 文書・図像類
• Title: 数値計算による複合エンジンの静止大気中における吸い込み性能予測
• Author/Editor: 河内, 俊憲; 苅田, 丈士; 富岡, 定毅; Kochi, Toshinori; Kanda, Takeshi; Tomioka, Sadatake
• Author Heading: 河内, 俊憲; 苅田, 丈士; 富岡, 定毅; Kochi, Toshinori; Kanda, Takeshi; Tomioka, Sadatake
• Publication, Distribution, etc.: 宇宙航空研究開発機構
• Publication Date: 2006-11-01
• Publication Date (W3CDTF): 2006-11-01
• Alternative Title: Numerical prediction of RBCC engine pumping performance under sea level static
• Periodical title: 宇宙航空研究開発機構特別資料: 平成18年度 宇宙航空研究開発機構 総合技術研究本部 宇宙科学研究本部 研究成果報告書 = JAXA Special Publication: Report on Research Achievements for FY2006 Institute of Space and Astronautical Science, Institute of Aerospace Technology, Japan Aerospace Exploration Agency
• No. or year of volume/issue: JAXA-SP-06-006
• Volume: JAXA-SP-06-006
• Pages: 93-98
• ISSN (Periodical Title): ISSN : 1349-113X
• Text Language Code: jpn
• Subject Heading: ロケットラムジェット複合エンジン; 計算機シミュレーション; ロケットエンジン設計; 推力測定; 性能試験; エジェクタジェットエンジン; 液体燃料ロケットエンジン; 燃焼室; 壁面圧; rocket-ramjet combined-cycle engine; computerized simulation; rocket engine design; thrust measurement; performance test; ejector jet engine; liquid propellant rocket engine; combustion chamber; wall pressure
• Target Audience: 一般
• Note (General): Numerical simulations were conducted to predict the ejector pumping performance of our rocket-ramjet combined-cycle engine under a take-off condition, which will be tested in the Ramjet Engine Test Facility at Fy2006. Our code was verified by comparing the numerical pumping performance with the measured one in the rectangular ejector with constant-area mixing duct. The numerical simulations in the combined-cycle engine revealed that when the engine was driven by cold N2 gas, the suction airflow was chocked at the exit of the engine throat at the rocket chamber pressure of 3 MPa. Above the pressure of 3 MPa, the suction airflow rate was decreased because the aerodynamic chocking was induced by the underexpanded rocket plume. When the ejector-driving gas was changed from cold N2 gas to hot combustion gas, the suction performance decreased remarkably. The numerical Mach contour distributions at the combustion gas injection showed that the rocket plume was remarkably converged in the constant-area mixing duct, as a comparison of the result at the N2 gas injection. The reason why the pumping performance decreased when the ejector was driven by the combustion gas was explained by the analysis of the ejector with constant area duct including heat and mole transfers. Our analysis of the ejector revealed that the heat transfer from hot rocket plume with supersonic speed to cold airflow with subsonic speed induced the expansion of the airflow and the pressure rise. This pressure rise was the reason why the pumping performance decreased when the ejector was driven by the combustion gas.; 資料番号: AA0049500020; レポート番号: JAXA-SP-06-006
• Access Restrictions: 限定公開
• Periodical Title (NCID): AA11984031; https://ci.nii.ac.jp/ncid/AA11984031
• Data Provider (Database): 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）; https://irdb.nii.ac.jp
• Original Data Provider (Database): 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