Transactions of the Korean Society of Mechanical Engineers A (대한기계학회논문집A)

The Korean Society of Mechanical Engineers (대한기계학회)
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Static Fluid-Structure Coupled Analysis of Low-Pressure Final-Stage Turbine Blade

발전용 저압터빈 최종단 블레이드의 정적 유체-구조 연계해석

  • Received : 2010.03.15
  • Accepted : 2010.06.16
  • Published : 2010.08.01
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Abstract

In this study, a loosely coupled fluid-structure interaction (FSI) analysis was conducted for a low-pressure (LP) final-stage rotor blade. Preliminary FSI analyses of a $15^{\circ}$ sweptback wing and a NASA Rotor 37 compressor blade were performed for verifying the boundary conditions. The results were compared with the established literatures for each model. The FSI analysis of the $15^{\circ}$ sweptback wing was carried out under both stable and unstable conditions. The excessive deformation of the wing was observed within 0.05 s under the unstable condition which is higher than the divergence speed of a wing compared with the stable condition. On the basis of the results of a steady-state study, an unsteady state FSI analysis was conducted for a NASA Rotor 37. Different deformations were observed at trailing edge of the blade in the static FSI and dynamic FSI analysis. A 3D FE model of a LP rotor was generated from the span-wise section data. In order to develop a reasonable model, an impact test was performed and compared to the FE model. Using this FE model, the steady-state FSI analysis was performed successfully.

본 논문에서는, 운전조건에서의 저압최종단 블레이드에 대하여 약결합 유체-구조 연계해석기법을 이용한 해석이 수행되었다. 저압터빈 최종단에 대한 해석이전에 경계조건에 대한 검증을 위하여 15도 후퇴익과 NASA Rotor 37을 대상으로 예비해석이 수행되었다. 각각의 해석결과들을 기존 문헌들과 비교하였다. 15도 후퇴익에 대한 안정상태와 불안정상태에서 동적 FSI해석이 수행되었다. 해석결과 변위가 일정한 안정상태에 비하여 고속에서는 0.05 초 만에 발산하는 결과를 산출하였다. NASA Rotor 37의 정상상태 해석결과를 바탕으로 정적 동적 FSI 해석을 수행하여 뒷전의 변형크기에 대하여 정적 FSI 결과와 동적 FSI간의 차이가 있음을 확인하였다. 저압 최종단 블레이드의 형상측정 및 동특성시험을 바탕으로 해석모델을 생성하였다. 이를 바탕으로, 운전조건에서 저압최종단 블레이드에 대한 정적 유체-구조 연계해석을 성공적으로 수행하였다.

Keywords

References

  1. Kim, H. J. and Park, J. Y., 1998, "Dynamic Analysis for Preventing Failures of Steam Turbine Blade," Journal of KFMA, Vol. 1, No. 1, pp. 17-23.
  2. Kim, H. S., Bae, Y. C., Kim, Y. H., Lee, H. and Kim, S. H., 2003, "Vibration Analysis for LP Turbine Blade Damage," Proceeding of Spring KSME Conference, pp. 752-757.
  3. Kim, Y. S., Kim, D. H., Kim, Y. H. and Park O., 2009, "Fluid/Structure Coupled Analysis of 3D Turbine Blade Considering Stator-Rotor Interaction," Journal of KSNVE, Vol. 19, No. 8, pp. 764-772. https://doi.org/10.5050/KSNVN.2009.19.8.764
  4. Kim, D. H., Kim, Y. S., Yang, G. W., Jung, K. K., Kim, K. H. and Min, D. G., 2009 "Flow-induced Vibration (FIV) Analysis of a 3D Axial Compressor Blade," Journal of KSNVE, Vol. 19, No. 6, pp. 551-559. https://doi.org/10.5050/KSNVN.2009.19.6.551
  5. Rzadkowski, R. and Gnesin, V., 2007, "3-D Inviscid Self-Excited Vibrations of a Blade Row in the Last Stage Turbine," Journal of Fluids and Structures, Vol. 23, Issue. 6, pp. 858-873. https://doi.org/10.1016/j.jfluidstructs.2006.12.003
  6. MSC/NASTRAN Aeroelastic Analysis User's Guide, Ver. 68.
  7. Foughner, J. T., Land, N. S. and Yates, E. C., 1963, "Use of Aerodynamic Parameters from Nonlinear Theory in Modified strip-Analysis Flutter Calculations for Finite-Span Wings At Supersonic Speeds," Langley Research Center, NASA-TN-D-1824.
  8. Tuovila, W. J. and McCarty, J. L., 1955, "Experimental Flutter Results for Cantilever-Wing Models at Mach Numbers up to 3.0," National Advisory Committee for Aeronautics Research Memorandum L55Ell.
  9. Kim, D. H. and Kim, Y. S., 2008, "Performance Evaluation of Stator-Rotor Cascade System Considering Flow Viscosity and Aeroelastic Deformation Effects," Journal of KSAS, Vol. 36, No. 1, pp. 72-78. https://doi.org/10.5139/JKSAS.2008.36.1.072
  10. McBean, I., Hourigan, K., Thompson, M. and Liu, F., 2005, "Prediction of Flutter of Turbine Blades in a Transonic Annular Cascade," Trans. of the ASME, Journal of Fluids Engineering, Vol. 127, Iss. 6, pp. 1053-1058. https://doi.org/10.1115/1.2060731
  11. Advisory Group for Aerospace Research and Development (AGARD), 1998, "CFD Validation for Propulsion System Components-Agard-AR-355," North Atlantic Treaty Organization (NATO).
  12. Kim, Y. S., Kim, D. H., Kim. Y. H. and Park, W., 2009, "Fluid/Structure Coupled Analysis of 3D Turbine Blade Considering Stator-rotor Intersaction," Journal of KSNVE, Vol. 19, No. 8, pp. 764-772. https://doi.org/10.5050/KSNVN.2009.19.8.764