0
Research Papers: Gas Turbines: Turbomachinery

Experimental Investigation of the Grouped Blade Vibration for Steam Turbine by Noncontact Sensors

[+] Author and Article Information
Tomomi Nakajima

Research & Development Center,
Mitsubishi Hitachi Power Systems, Ltd.,
Saiwai-cho 3-1-1, Hitachi,
Ibaraki 317-0073, Japan
e-mail: tomomi_nakajima@mhps.com

Kiyoshi Segawa

Research & Development Center,
Mitsubishi Hitachi Power Systems, Ltd.,
Saiwai-cho 3-1-1, Hitachi,
Ibaraki 317-0073, Japan
e-mail: kiyoshi_segawa@mhps.com

Hiromichi Kitahara

Turbomachinery Headquarters,
Mitsubishi Hitachi Power Systems, Ltd.,
Saiwai-cho 3-1-1, Hitachi,
Ibaraki 317-0073, Japan
e-mail: hiromichi_kitahara@mhps.com

Akimitsu Seo

Turbomachinery Headquarters,
Mitsubishi Hitachi Power Systems, Ltd.,
Saiwai-cho 3-1-1, Hitachi,
Ibaraki 317-0073, Japan
e-mail: akimitsu_seo@mhps.com

Yutaka Yamashita

Turbomachinery Headquarters,
Mitsubishi Hitachi Power Systems, Ltd.,
Saiwai-cho 3-1-1, Hitachi,
Ibaraki 317-0073, Japan
e-mail: yutaka1_yamashita@mhps.com

Takeshi Kudo

Turbomachinery Headquarters,
Mitsubishi Hitachi Power Systems, Ltd.,
Saiwai-cho 3-1-1, Hitachi,
Ibaraki 317-0073, Japan
e-mail: takeshi_kudo@mhps.com

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 27, 2017; final manuscript received August 23, 2017; published online January 10, 2018. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(5), 052603 (Jan 10, 2018) (7 pages) Paper No: GTP-17-1406; doi: 10.1115/1.4038282 History: Received July 27, 2017; Revised August 23, 2017

All turbine blades have mistuned structures caused by manufacturing variations within the manufacturing tolerance, such as the geometrical deviations and variance of material properties. The mistuning effect has a known tendency to increase the dynamic stress, but it is also known to be difficult to predict the maximum vibration response before the operation. This paper studies the blade vibration of grouped blades in a low-pressure steam turbine. The study objectives are to characterize the vibration behavior of the grouped blade structure and to evaluate the maximum response of all blades in a stage experimentally. An experimental investigation is carried out in a vacuum chamber, and blades are excited by an air jet during start-up and shut-down. The circumferential blade amplitude distribution is measured by noncontact sensors (NCSs) and strain gauges (SGs). The circumferential blade amplitude distribution is found to differ depending on vibration modes and nodal diameters (NDs), but the relative tendency is almost the same for all types of operation at each mode and all NDs. Therefore, the median of all experimental results obtained with the NCSs is used in a comparison with calculation results and results of two theoretical curves obtained using equations from the literature. In comparing the measurement results and the calculation results, the circumferential blade amplitude distribution is not the same with all modes and NDs. However, the maximum amplitude magnification is about 1.5–1.8, and all measurement results are lower than the results for the two theoretical equations. This means the maximum response comparison to the tuned blade gives an evaluation on the safe side by the two theoretical equations.

FIGURES IN THIS ARTICLE
<>
Copyright © 2018 by ASME
Your Session has timed out. Please sign back in to continue.

References

Gloger, M. , Neumann, K. , and Termuehlen, H. , 1986, Design Criteria for Reliable Low-Pressure Blading, The American Society of Mechanical Engineers, New York, pp. 1–9.
Szwedowicz, J. , Secall-Wimmel, T. , Dünck-Kerst, P. , Sonnenschein, A. , Regnery, D. , and Westfahl, M. , 2007, “Scaling Concept for Axial Turbine Stages With Loosely Assembled Friction Bolts: The Linear Dynamic Assessment—Part 1,” ASME Paper No. GT2007-27502.
Weaver, F. L. , and Prohl, M. A. , 1958, “High-Frequency Vibration of Steam-Turbine Buckets,” Trans. ASME, 80, pp. 181–194.
Wagner, L. F. , and Griffin, J. H. , 1996, “Forced Harmonic Response of Grouped Blade Systems—Part 1: Discrete Theory,” ASME J. Eng. Gas Turbines Power, 118(1), pp. 130–136. [CrossRef]
Kaneko, Y. , Mori, K. , Watanabe, E. , and Nagashima, T. , 1997, “Vibrational Response Analysis of a Mistuned Bladed Disk (Grouped Blade),” Jpn. Soc. Mech. Eng., C, 63(610), pp. 1887–1892. [CrossRef]
Rzadkowski, R. , Maurin, A. , Kubitz, L. , and Szczepanik, R. , 2016, “Forced Vibration of Mistuned Bladed Discs in Last Stage LP Steam Turbine,” ASME Paper No. GT2016-57427.
Afolabi, D. , 1988, “A Note on the Rogue Failure of Turbine Blades,” J. Sound Vib., 122(3), pp. 535–545. [CrossRef]
Petrov, E. P. , and Ewins, D. J. , 2003, “Analysis of the Worst Mistuning Patterns in Bladed Disk Assemblies,” ASME J. Turbomach., 125(4), pp. 623–631. [CrossRef]
Whitehead, D. S. , 1966, “Effect of Mistuning on the Vibration of Turbomachine Blades Induced by Wakes,” J. Mech. Eng. Sci., 8(1), pp. 15–20. [CrossRef]
Kenyon, J. A. , and Griffin, J. H. , 2001, “Forced Response of Turbine Engine Bladed Disks and Sensitivity to Harmonic Mistuning,” ASME Paper No. GT2001-0274.
Hemberger, D. , Filsinger, D. , and Bauer, H.-J. , 2012, “Investigating on Maximum Amplitude Amplification Factor of Real Mistuned Bladed Structures,” ASME Paper No. GT2012-68084.
Heinz, C. , Schatz, M. , Casey, M. , and Stüer, H. , 2011, “Impact of Mistuning on the Vibration Behaviour of the Last Stage in a Model Three Stage Low Pressure Steam Turbine,” ASME Paper No. GT2011-45784.
Drozdowski, R. , Völker, L. , Häfele, M. , and Vogt, D. M. , 2015, “Experimental and Numerical Investigation of the Nonlinear Vibrational Behavior of Steam Turbine Last Stage Blades With Friction Bolt Damping Elements,” ASME Paper No. GT2015-42244.
Pohle, L. , Scheidt, L. P. , Wallaschek, J. , Aschenbruck, J. , and Seume, J. R. , 2014, “Dynamic Behavior of a Mistuned Air Turbine: Comparison Between Simulations and Measurements,” ASME Paper No. GT2014-26025.
Saito, E. , Namura, K. , Takasumi, M. , Okabe, A. , and Ikeuchi, K. , 1993, “Vibration Characteristics of Turbine Blades With Compound Periodic Structure,” Jpn. Soc. Mech. Eng., C, 59(567), pp. 3275–3282. [CrossRef]
Saito, E. , Namura, K. , and Okabe, A. , 1993, “Resonance Characteristics of Turbine Blades With Compound Periodic Structure,” International Conference on Power Engineering, Tokyo, Japan, Sept. 12–16, pp. 449–454.
Hartung, A. , and Hackenberg, H.-P. , 2016, “A Practical Approach for Evaluation of Equivalent Linear Damping From Measurements of Mistuned and/or Non-linear Stages and Forced Response Validation,” ASME Paper No. GT2016-56435.
Anding, D. , Ressing, H. , Hörmeyer, K. , Pisch, R. , and Ziegler, K. , 2014, “Development of a Novel Axial Compressor Generation for Industrial Applications—Part 2: Blade Mechanics,” ASME Paper No. GT2014-26246.
Kharyton, V. , and Bladh, R. , 2014, “Using Tiptiming and Strain Gauge Data for the Estimation of Consumed Life in a Compressor Blisk Subjected to Stall-Induced Loading,” ASME Paper No. GT2014-27251.
Kariya, D. , Yamamoto, T. , and Ishihara, K. , 2009, “A Blade Resonance Prediction Using Fluid-Structure Interaction Calculation Method and Comparison With the Test,” ASME Paper No. GT2009-59460.
Sato, K. , Takasumi, M. , Kashiwabara, Y. , and Toriya, H. , 1994, “Measurements of Blade Vibration for a Compressor Using a Noncontact Measurement System,” GTSJ Jpn. Soc. Mech. Eng., 22(86), pp. 48–54.
Zielinski, M. , and Ziller, G. , 2005, “Noncontact Blade Vibration Measurement System for Aero Engine Application,” 17th International Symposium on AirBreathing Engines, Munich, Germany, Sept. 4–9, Paper No. ISABE-2005-1220.
Kenyon, J. A. , and Griffin, J. H. , 2003, “Experimental Demonstration of Maximum Mistuned Bladed Disk Forced Response,” ASME Paper No. GT2003-38060.
Kulkarni, A. , and LaRue, G. , 2008, “Vibratory Response Characterization of a Radial Turbine Wheel for Automotive Turbocharger Application,” ASME Paper No. GT2008-51355.
Schoenenborn, H. , Retze, U. , Ziller, G. , and Waniczek, P. , 2010, “Experimental and Analytical Mistuning Analysis of a Blisk at Lab Conditions and Under Rig Conditions Using Tip Timing,” ASME Paper No. GT2010-22447.
Heinz, C. , Schatz, M. , Casey, M. , and Stüer, H. , 2010, “Experimental and Analytical Investigations of a Low Pressure Model Turbine During Forced Response Excitation,” ASME Paper No. GT2010-22146.
Dickmann, H.-P. , Wimmel, T. S. , Szwedowicz, J. , Filsinger, D. , and Roduner, C. H. , 2005, “Unsteady Flow in a Turbocharger Centrifugal Compressor: 3D-CFD-Simulation and Numerical and Experimental Analysis of Impeller Blade Vibration,” ASME Paper No. GT2005-68235.
Rossi, M. R. , Feiner, D. M. , and Griffin, J. H. , 2005, “Experimental Study of the Fundamental Mistuning Model for Probabilistic Analysis,” ASME Paper No. GT2005-68127.
Sever, I. A. , Petrov, E. E. , and Ewins, D. J. , 2007, “Experimental and Numerical Investigation of Rotating Bladed Disk Forced Response Using Under-Platform Friction Dampers,” ASME Paper No. GT2007-27307.

Figures

Grahic Jump Location
Fig. 1

Finite element model of steam turbine bladed disk

Grahic Jump Location
Fig. 2

An example set of response curves for the same blade

Grahic Jump Location
Fig. 3

Comparison of peak amplitudes measured by NCSs and SGs

Grahic Jump Location
Fig. 4

All results measured by NCSs

Grahic Jump Location
Fig. 5

Standard deviation of maximum response measured by NCSs

Grahic Jump Location
Fig. 6

Measurement results by NCSs and calculation results (data of all blades)

Grahic Jump Location
Fig. 7

Measurement results by NCSs and calculation results (data of each group)

Grahic Jump Location
Fig. 8

Maximum amplification factor

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In