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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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References

Figures

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Fig. 4

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

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Fig. 3

Refraction of sound by a shear layer, acoustic blade excitation

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Fig. 6

Test setup and investigation parameters

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Fig. 5

Instrumented AETR cascade

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Fig. 2

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

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Fig. 1

Possibility of acoustic excitation in a rotating test rig

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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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