TAILIEUCHUNG - Experimental and numerical modal analysis of the first and second stage compressor blades

In this paper, the first and second stage compressor blades of a gas turbine were studied by the experimental and numerical modal analyses. | Nội dung Text Experimental and numerical modal analysis of the first and second stage compressor blades Engineering Solid Mechanics 7 2019 341-354 Contents lists available at GrowingScience Engineering Solid Mechanics homepage esm Experimental and numerical modal analysis of the first and second stage compressor blades Seyed Mohammad Navid Ghoreishia Mohammad Salarib Seyed Majid Pourhosseinic and Aram Bahmanid a Satellite Research Institute Iranian Space Research Center Tehran Iran b Faculty of Engineering Department of Applied Mechanics University of Qom Qom Iran c Faculty of Mechanical Engineering . Toosi of Tech Tehran Iran d Department of Mechanical and Mechateronics Engineering University of Waterloo Waterloo Ontario Canada A R T I C L EI N F O ABSTRACT Article history In this paper the first and second stage compressor blades of a gas turbine were studied by the Received 25 December 2018 experimental and numerical modal analyses. At first the geometric models of these blades were Accepted 17 June 2019 generated by the 3D scanner and then the mode shapes and the natural frequencies of each blade Available online were extracted by a series of numerical modal analyses. The numerical results were compared with 17 June 2019 Keywords the data obtained from the experimental modal analysis and the validity and accuracy of the Compressor blade developed numerical models were confirmed. Unlike most studies that use fixed-free boundary Modal analysis condition for performing a modal analysis this objective was pursued by applying a free-free Natural frequency boundary condition. This study also investigated the effect of using wax or glue for mounting the Numerical analysis accelerometer on the blade by assessing the FRF curves obtained from the modal tests in the Experimental analysis frequency range of 0-10000 Hz. The sensitivity of the test results to applying free-free boundary condition the number of accelerometers and their positions .

• Cơ khí - Chế tạo máy
• Analysis of the compressor blades
• The first and second stage compressor blades of a gas turbine
• Compressor blades of a gas turbine
• The studied compressor blade
• The geometric models of blades