EFFECTS OF NEIGHBORING BLADE ROW ON SUPERSONIC CASCADE FLUTTER

相邻叶片排对超声速级联颤振的影响

• 批准号: 13650964
• 负责人: NAMBA Masanobu
• 金额: $ 2.62万
• 依托单位: Sojo University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (C)
• 财政年份: 2001
• 资助国家: 日本
• 起止时间: 2001 至 2003
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-13650964/
• 关键词: UNSTEADY AERODYNAMICS; AEROELASTICITY; FLUTTER; CASCADE; CONTRA-ROTATING CASCADES; BLADE ROW INTERACTION; AEROACOUSTICS; UNSTEADY LIFTING SURFACE THEORY; 動静翼列干渉; 非定常学

An unsteady lifting surface theory was developed for contra-rotating annular blade rows with vibrating blades. A program was coded to compute unsteady aerodynamic force and work on blades for specified frequency, inter-blade phase angle and other design parameters. The program is comprehensive, and it can deal with various combinations of blade rows, i.e., combinations of subsonic and subsonic blade rows, supersonic and supersonic blade rows, and subsonic and supersonic blade rows. The validity of the program was confirmed by making a comparison for a model condition between the results from the present program and those of CFD Euler code computation conducted by Professor K.C.Hall of Duke University. Both results were in complete agreement.Parametric studies were conducted to investigate the influence of the neighboring blade rows on unsteady loading caused by blade vibration.A computation program was coded to determine the critical condition of occurrence of coupled bending-torsion f … More lutter, which utilizes the above mentioned program as a subprogram to calculate unsteady aerodynamic force terms in flutter equations. The influence of the neighboring blade row on the flutter boundaries was investigated.New findings are summarized as follows.(1)Vibrating subsonic blade row : Unsteady aerodynamic work on vibrating blades, critical flutter velocity, critical flutter frequency and flutter mode are substantially influenced by the presence of a neighboring blade row in cases where the fundamental acoustic duct mode generated from the vibrating blade row is cut-on. On the other hand in cases where the fundamental acoustic duct mode is cut-off, the influence of the neighboring blade row is essentially small unless the blade row gap is very small.(2)Vibrating supersonic blade row : Unsteady aerodynamic work on vibrating blades, critical flutter velocity, critical flutter frequency and flutter mode are very sensitive to parametric change near the resonance points of low order acoustic duct modes. The behaviors of the variations with the parametric change are heavily influenced by the presence of the neighboring blade row. Less

建立了振动叶片对转环形叶列的非定常升力面理论。编制了计算程序，计算了给定频率、叶间相位角等设计参数下的非定常气动力和叶片做功。该程序综合性强，可处理各种叶排组合，即，亚音速和亚音速叶片排、超音速和超音速叶片排以及亚音速和超音速叶片排的组合。通过将本程序的计算结果与杜克大学K.C.Hall教授的CFD Euler程序计算结果进行比较，确认了程序的有效性。通过参数分析，研究了相邻叶排对叶片振动引起的非定常载荷的影响，编制了计算程序，确定了发生弯扭耦合振动的临界条件，并对计算结果进行了分析 ...更多信息 吕特lutter，它利用上述程序作为子程序计算颤振方程中的非定常气动力项。研究了相邻叶排对颤振边界的影响，新的研究结果总结如下。（1）振动亚音速叶栅：在从振动叶片排产生的基本声导管模式被切断的情况下，振动叶片上的非定常空气动力功、临界颤振速度、临界颤振频率和颤振模式的存在受到相邻叶片排的显著影响。另一方面，在基本声导管模式被切断的情况下，相邻叶片排的影响基本上很小，除非叶片排间隙非常小。（2）振动超声速叶栅：振动叶片上的非定常气动力功、临界颤振速度、临界颤振频率和颤振模态对低阶声导管模态共振点附近的参数变化非常敏感。相邻叶列的存在严重影响了随参数变化的变化行为。少

项目成果

難波昌伸: "Recent Findings of Analytical Studies in Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines"Proceedings of International Gas Turbine Congress 2003 Tokyo. IGTC2003 Tokyo Ks-6. (2003)

Masanobu Namba：“涡轮机非定常空气动力学、气动声学和气动弹性分析研究的最新发现”2003 年东京国际燃气轮机大会论文集（IGTC2003 东京 Ks-6）。

Masanobu NAMBA, Ryohei NISHINO: "Flutter Analysis of Annular Cascades in Counter Rotation"Proceedings of Asian Joint Conference on Propulsion and Power. (2004)

Masanobu NAMBA、Ryohei NISHINO：“反向旋转环形叶栅的颤振分析”亚洲推进与动力联合会议论文集。

Masanobu NAMBA: "Unsteady Aerodynamic Work on Oscillating Annular Cascades in Counter Rotation"Proceedings of 10^<th> International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines. (2004)

Masanobu NAMBA：“反向旋转中振荡环形叶栅的非定常空气动力学工作”第十届涡轮机非定常空气动力学、气动声学和气动弹性国际研讨会论文集。

難波昌伸: "What is the Role of Analytical Methods in Modern Unsteady Aerodynamics of Turbomachines"Proceedings of 9^<th> International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines. 12-23 (2001)

Masanobu Namba：“分析方法在涡轮机现代非定常空气动力学中的作用”第 9 届涡轮机非定常空气动力学、气动声学和气动弹性国际研讨会论文集 12-23 (2001)。

Masanobu NAMBA: "Unsteady Aerodynamic Response of Oscillating Supersonic Annular Cascades in Counter Rotation"AIAA Meeting Papers on Disk : The 37^<th> AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Vol.6, No.3. (2001)

Masanobu NAMBA：“反向旋转中振荡超音速环形叶栅的不稳定空气动力学响应”AIAA 会议论文磁盘：第 37 届 AIAA/ASME/SAE/ASEE 联合推进会议。