An inlet distortion due to a vortexlike turbulent wake interfering aerodynamically with walls of a narrow channel as a gas-turbine one.

由于涡旋状湍流尾流在空气动力学上干扰燃气轮机狭窄通道的壁而导致的入口变形。

• 批准号: 61550045
• 负责人: SUGIYAMA Yoshiyuki
• 金额: $ 1.41万
• 依托单位: Nagoya University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for General Scientific Research (C)
• 财政年份: 1986
• 资助国家: 日本
• 起止时间: 1986 至 1987
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-61550045/
• 关键词: Fluid mechanics; Gas-turbine internal flow; Confined turbulent wake; Secondary flow; Deflected jet trajectory; Inlet distortion; Aerodynamic wall-interference; 壁面空力干渉; 速度ベクトル測定; 流れのディストーション; 流れの渦構造; 三次元流; 流路壁の空力的干渉; 熱線応答式の解法; 後流; 渦糸の誘導速度

Considerations are made on the flow distortion resulting from two kinds of obstacle, which extends across a narrow channel. They are a jet issuing normally into a cross flow from a channel wall and a cylinder spanned between channel walls.1. On the jet (1) Analyses ---- The following are discussed, namely, effects of a wall boundary layer on a trajectory of the jet issuing across the boundary layer f a trajectory of the jet impinging on the channel wall ; a circulation along the vortexlike flow induced by the jet ; aerodynamic wall-interference effects and a trajectory of the jet. The calculated and experimental jet-trajectories agree fairly good. The calculated circulation is near experiments, especially at low velocity ratios. The distortion of the velocity field can be calculated using Biot-Savart's law, together with the vortex center line and the circulation along it. The calculated velocity distributions agree quontitatively with experiments. (2) Experiments ---- Considerations a … More re made on a three-dimensional flow, which results from both a vortexlike flow induced by the jet impinging on a channel wall and aerodynamic interference effects due to the vortexlike flow and the channel wall. The result gives new knowledges on a variation of the maximum velocity along the jet center line, a location of the vortex center line downstream of an impinging point of the jet, and a flow pattern on the channel wall, on which the jet impinges.2. On the cylinder (1) Experiments ---- The flow distortion due to the cylinder, a channel-wall boundary layer and aerodynamic wall-interference effects is considered. Velocity vectors are measured with the hot-wire anemometer. The necklacelike vortex as a secondary flow isn't clear, because of a small wall-boundary-layer thickness. However, the results reveal that there is the interference effects due to the cylinder and the wall boundary layer, especially the marked effects on the lateral velocity component. Topics for further investigation are to derive an empirical expression for trajectories of the necklacelike vortex and to improve a hot-wire technique for measurements of velocity vector with large fluctuations. Less

Considerations are made on the flow distortion resulting from two kinds of obstacle, which extends across a narrow channel. They are a jet issuing normally into a cross flow from a channel wall and a cylinder spanned between channel walls.1. On the jet (1) Analyses ---- The following are discussed, namely, effects of a wall boundary layer on a trajectory of the jet issuing across the boundary layer f a trajectory of the jet impinging on the channel wall ; a circulation along the vortexlike flow induced by the jet ; aerodynamic wall-interference effects and a trajectory of the jet. The calculated and experimental jet-trajectories agree fairly good. The calculated circulation is near experiments, especially at low velocity ratios. The distortion of the velocity field can be calculated using Biot-Savart's law, together with the vortex center line and the circulation along it. The calculated velocity distributions agree quontitatively with experiments. (2) Experiments ---- Considerations a … More re made on a three-dimensional flow, which results from both a vortexlike flow induced by the jet impinging on a channel wall and aerodynamic interference effects due to the vortexlike flow and the channel wall. The result gives new knowledges on a variation of the maximum velocity along the jet center line, a location of the vortex center line downstream of an impinging point of the jet, and a flow pattern on the channel wall, on which the jet impinges.2. On the cylinder (1) Experiments ---- The flow distortion due to the cylinder, a channel-wall boundary layer and aerodynamic wall-interference effects is considered. Velocity vectors are measured with the hot-wire anemometer. The necklacelike vortex as a secondary flow isn't clear, because of a small wall-boundary-layer thickness. However, the results reveal that there is the interference effects due to the cylinder and the wall boundary layer, especially the marked effects on the lateral velocity component. Topics for further investigation are to derive an empirical expression for trajectories of the necklacelike vortex and to improve a hot-wire technique for measurements of velocity vector with large fluctuations.较少的

项目成果

杉山善幸: 第23回日本航空宇宙学会,中部・関西支部合同秋期大会講演集. 70-73 (1986)

Yoshiyuki Sugiyama：第 23 届日本航空学会中部/关西分会秋季联合会议论文集（1986 年）。

杉山善幸: 第23回日本航空宇宙学会,中部・関西支部合同秋期大会講演集. 66-69 (1986)

Yoshiyuki Sugiyama：日本航空学会第 23 届中部关西分会联合秋季会议记录 66-69 (1986)。

杉山善幸: Memoirs of the Faculty of Engineering,Nagoya University-Research Report. 2Vol.38,NO.233-246 (1986)

杉山义行：名古屋大学工学部回忆录-研究报告2Vol.38，NO.233-246（1986）。