Research Papers

Impact of the Flow on an Acoustic Excitation System for Aeroelastic Studies

[+] Author and Article Information
Michael Bartelt, Joerg R. Seume

Institute of Turbomachinery
and Fluid Dynamics,
Leibniz University Hannover,
Appelstrasse 9,
Hannover DE-30167, Germany

Marc Mittelbach

Siemens AG,
Energy Sector,
Mellinghofer Str. 55,
Muelheim an der Ruhr DE-45473, Germany

Matthew Montgomery

Siemens Energy, Inc.,
4400 Alafaya Trail,
Orlando, FL 32826

Damian M. Vogt

Royal Institute of Technology,
Department of Energy Technology,
Stockholm S-10044, Sweden

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received July 12, 2012; final manuscript received August 1, 2012; published online March 25, 2013. Editor: David Wisler.The content of this paper is copyrighted by Siemens Energy, Inc. and is licensed to ASME for publication and distribution only. Any inquiries regarding permission to use the content of this paper, in whole or in part, for any purpose must be addressed to Siemens Energy, Inc. directly.

J. Turbomach 135(3), 031033 (Mar 25, 2013) (9 pages) Paper No: TURBO-12-1139; doi: 10.1115/1.4007511 History: Received July 12, 2012; Revised August 01, 2012

The flow in turbomachines is highly unsteady. Effects like vortices, flow separation, and shocks are an inevitable part of the turbomachinery flow. Furthermore, high blade aspect ratios, aerodynamically highly loaded and thin profiles increase the blade sensitivity to vibrations. According to the importance of aeroelasticity in turbomachines, new strategies for experimental studies in rotating machines must be developed. A basic requirement for aeroelastic research in rotating machines is to be able to excite the rotor blades in a defined manner. Approaches for active blade excitation in running machines may be piezoelectric elements, magnetism, or acoustics. Contact-free excitation methods are preferred, since additional mistuning is brought into the investigated system otherwise. A very promising method for aeroelastic research is the noncontact acoustic excitation method. In this paper, investigations on the influence of an annular cascade flow on the blade vibration, excited by an acoustic excitation system, are presented for the first time. These investigations are carried out at the Aeroelastic Test Rig of the Royal Institute of Technology in Stockholm. By varying the excitation angle, the outlet Mach number, and the relative position of the excited blade to the excitation system, the influence of the flow on the acoustic excitation is quantified. The results show that there is a strong dependency of the excited vibration amplitude on the excitation angle if the outlet Mach number is increased, which implies that preferable excitation directions exist. Furthermore, it is shown that a benefit up to 23% in terms of excited vibration amplitude can be reached if the flow velocity is raised.

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Hall, K. C., Thomas, J. P., and Clark, W. S., 2002, “Computation of Unsteady Nonlinear Flows in Cascades Using a Harmonic Balance Technique,” AIAA J., 40, pp. 879–886. [CrossRef]
Corral, R., Gallardo, J. M., and Vasco, C., 2007, “Aeroelastic Stability of Welded-in-Pair Low Pressure Turbine Rotor Blades: A Comparative Study Using Linear Methods,” ASME J. Turbomach., 129, pp. 72–83. [CrossRef]
Kersken, H.-P., Frey, C., Voigt, C., and Ashcroft, G., 2010, “Time-Linearized and Time-Accurate 3D RANS Methods for Aeroelastic Analysis in Turbomachinery,” Proceedings of ASME Turbo Expo 2010: Power for Land, Sea and Air, ASME Paper No. GT2010-22940. [CrossRef]
Bölcs, A., and Fransson, T. H., 1986, “Aeroelasticity in Turbomachines—Comparison of Theoretical and Experimental Results,” Communication du Laboratoire de Thermique Appliqué et de Turbomachines, Vol. 13, Ecole Polytechnique Fédérale de Lausanne, Lausanne, Switzerland.
Vogt, D. M., and Fransson, T. H., 2007, “Experimental Investigation of Mode Shape Sensitivity of an Oscillating Low-Pressure Turbine Cascade at Design and Off-Design Conditions,” ASME J. Eng. Gas Turbines Power, 129, pp. 530–541. [CrossRef]
Belz, J., and Hennings, H., 2000, “Aerodynamic Stability Investigations of an Annular Compressor Cascade Based on Unsteady Pressure Measurements,” Proceedings of the 9th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines, Lyon, France, September 4–8, pp. 280–295.
Marshall, J. G., and Imregun, M., 1996, “A Review of Aeroelasticity Methods With Emphasis on Turbomachinery Applications,” J. Fluids Struct., 10, pp. 237–267. [CrossRef]
Sanders, A. J., Rabe, D., and Fost, R., 2002, “An Experimental Investigation of Stall Flutter in an Advanced Design Low-Aspect Ratio Fan Blisk,” Proceedings 7th National Turbine Engine High Cycle Fatigue Conference, Palm Beach, FL, May 11–15.
Manwaring, S. R., Rabe, D. C., Lorence, C. B., and Wadia, A. R., 1996, “Inlet Distortion Generated Forced Response of a Low Aspect-Ratio Transonic Fan,” Proceedings of ASME Turbo Expo 1996: Power for Land, Sea and Air, Birmingham, UK, June 10–13, ASME Paper No. 96-GT-376.
Rice, T., Bell, D., and Singh, G., 2007, “Identification of the Stability Margin Between Safe Operation and the Onset of Blade Flutter,” Proceedings of ASME Turbo Expo 2007: Power for Land, Sea and Air, ASME, Paper No. GT2007-27462. [CrossRef]
Siemann, J., Nollau, R., Grüber, B., and Seume, J. R., 2009, “Controlled Excitation of Rotor Blades via Macro Fiber Composites in an Axial Compressor,” Proceedings of XIX International Symposium on Air Breathing Engines, Montreal, Canada, September 7–11, Paper No. ISABE-2009-1263.
Jones, K., and Cross, C., 2002, “A Traveling Wave Excitation System for Bladed Disks,” 43rd AIAA/ASME/ASCE/AHS Structures, Structural Dynamics, and Materials Conference, Paper No. AIAA 2002-1531 [CrossRef].
Pierre, C., Ceccio, S. L., Judge, J., and Cross, C. J., 2000, “Experimental Investigation of Mistuned Bladed Disk Vibration,” Proceedings for the 5th National Turbine Engine High Cycle Fatigue Conference, Chandler, AZ, March 7–9.
Amiet, R. K., 1978, “Refraction of Sound by Shear Layer,” J. Sound Vib., 58, pp. 467–482. [CrossRef]
Ahuja, K. K., Tester, B. J., and Tanna, H. K., 1978, “The Free Jet as a Simulator of Forward Velocity Effects on Jet Noise,” NASA Contractor Report No. 3056.
Schlinker, R. H., and Amiet, R. K., 1979, “Refraction of Sound by a Shear Layer—Experimental Assessment,” AIAA 5th Aeroacoustics Conference, Seattle, WA, March 12–14, Paper No. 79-0628. [CrossRef]
Vogt, D. M., 2005, “Experimental Investigations of Three-Dimensional Mechanisms in Low-Pressure Turbine Flutter,” Ph.D. thesis, Kungliga Tekniska Högskolan, Stockholm.
Vogt, D. M., and Fransson, T. M., 2004, “A Technique for Using Recessed-Mounted Pressure Transducers to Measure Unsteady Pressure,” 17th Symposium on Measuring Techniques in Transonic and Supersonic Flow in Cascades and Turbomachines, Stockholm, Sweden, September 9–10.


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Fig. 1

Possibility of acoustic excitation in a rotating test rig

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Fig. 2

Refraction of sound by a shear layer (Amiet [14])

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Fig. 3

Refraction of sound by a shear layer, acoustic blade excitation

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Fig. 4

Propagation angle (a) and sound pressure amplitude correction (b)

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Fig. 5

Instrumented AETR cascade

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Fig. 6

Test setup and investigation parameters

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Fig. 7

Excited vibration amplitude: I) suction side excitation, II) upstream excitation, III) pressure side excitation

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Fig. 8

Blade eigenfrequency in dependence on Ma2

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Fig. 9

Arcwise coordinate of AETR blade profile (Vogt [17])

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Fig. 10

Distribution of unsteady pressure amplitude

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Fig. 11

Maximum achievable vibration amplitude for different excitation angles




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