0
Research Papers

Prediction of Turbomachinery Aeroelastic Behavior From a Set of Representative Modes

[+] Author and Article Information
Damian M. Vogt, Torsten H. Fransson

Royal Institute of Technology,
Heat and Power Technology,
S-100 44 Stockholm, Sweden

Hans Mårtensson

VOLVO Aero Corporation,
S-461 81 Trollhättan, Sweden

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 10, 2011; final manuscript received August 23, 2011; published online October 30, 2012. Editor: David Wisler.

J. Turbomach 135(1), 011032 (Oct 30, 2012) (11 pages) Paper No: TURBO-11-1180; doi: 10.1115/1.4006536 History: Received August 10, 2011; Revised August 23, 2011

A method is proposed for the determination of the aeroelastic behavior of a system responding to mode-shapes which are different from the tuned in vacuo ones, due to mistuning, mode family interaction, or any other source of mode-shape perturbation. The method is based on the generation of a data base of unsteady aerodynamic forces arising from the motion of arbitrary modes and uses least square approximations for the prediction of any responding mode. The use of a reduced order technique allows for mistuning analyses and is also applied for the selection of a limited number of arbitrary modes. The application of this method on a transonic compressor blade shows that the method captures the aeroelastic properties well in a wide frequency range. A discussion of the influence of the mode-shapes and frequency on the final stability response is also provided.

© 2013 by ASME
Your Session has timed out. Please sign back in to continue.

References

Crawley, E., “Aeroelastic Formulation for Tuned and Mistuned Rotors,” AGARD Manual on Aeroelasticity in Axial-Flow Turbomachines (Structural Dynamics and Aeroelasticity, Vol. 2), AGARD, Neuilly sur Seine, France.
Kielb, R. E., Hall, K. C., Miyakozawa, T., 2007, “The Effect of Unsteady Aerodynamic Asymmetric Perturbations on Flutter,” Proceedings of ASME Turbo Expo (GT2007), ASME Paper No. GT2007-27503. [CrossRef]
Miyakozawa, T., Kielb, R., and Hall, K., 2008, “The Effects of Aerodynamic Asymmetric Perturbations on Forced Response Bladed Disks,” Proceedings of Turbo Expo (GT2008), ASME Paper No. GT2008-50719. [CrossRef]
Martel, C., Corral, R., and Llorens, J., 2008, “Stability Increase of Aerodynamically Unstable Rotors Using Intentional Mistuning,” ASME J. Turbomach., 130, p. 011006. [CrossRef]
Martel, C. and Corral, R., 2009, “Asymptotic Description of Maximum Mistuning Amplification of Bladed Disk Forced Response,” ASME J. Eng. Gas Turbines Power, 131, p. 022506. [CrossRef]
Gerolymos, G. A., 1993, “Coupled Three-Dimensional Aeroelastic Stability Analysis of Bladed Disks,” ASME J. Turbomach., 115, pp. 791–799. [CrossRef]
Mårtensson, H., Gunnsteinsson, S., and Vogt, D., 2008, “Aeroelastic Properties of Closely Spaced Modes for a Highly Loaded Transonic Fan,” Proceedings of ASME Turbo Expo (GT2008), ASME Paper No. GT2008-51046. [CrossRef]
Clark, S., Kielb, R., and Hall, K., 2009, “The Effect of Mass Ratio, Frequency Separation, and Solidity on Multi-Mode Fan Flutter,” Proceedings of the 12th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines (ISUAAAT 12), Imperial College, London, September 1–4, Paper No. I12-S3-2.
Mayorca, M., Vogt, D., Mårtensson, H., and Fransson, T., 2010, “A New Reduced Order Modeling for Stability and Forced Response Analysis of Aero-Coupled Blades Considering Various Mode Families,” Proceedings of ASME Turbo Expo (GT2010), ASME Paper No. GT2010-22745. [CrossRef]
Glodic, N., Bartelt, M., Vogt, D., and Fransson, T., 2009, “Aeroelastic Properties of Combined Mode Shapes in an Oscillating LPT Cascade,” Proceedings of the 12th International Symposium on Unsteady Aerodynamics, Aeronautics and Aeroelasticiy in Turbomachines (ISUAAAT 12), Imperial College, London, September 1–4, Paper No. I12-S8-2.
Guyan, R., 1965, “Reduction Stiffness and Mass Matrices,” AIAA J., 3(2), p. 380. [CrossRef]
Mårtensson, H., 2005, “A Method for Deriving an Aeroelastic Model from Harmonic CFD results,” Paper No. ISABE2005-1255.
Mårtensson, H., Burman, J., and Johansson, U., 2007, “Design of the High Pressure Ratio Transonic 1-1/2 Stage Fan Demonstrator Hulda,” ASME Paper No. GT2007-27793. [CrossRef]
Eriksson, L. E., 1993, “A Third Order Accurate Upwind-Based Finite-Volume Scheme for Unsteady Compressible Viscous Flow,” Technical Report, VAC Report No. 9370-154, Volvo Aero Corporation, Trollhättan, Sweden.
Mayorca, M., Vogt, D., Mårtensson, H., and Fransson, T., 2009, “Numerical Tool for Prediction of Aeromechanical Phenomena in Gas Turbines,” Paper No. ISABE-2009-1250.

Figures

Grahic Jump Location
Fig. 1

Structural rotor blade mesh

Grahic Jump Location
Fig. 2

First seven real modes and frequencies. Frequency range considered: f1 − f7.

Grahic Jump Location
Fig. 3

Steady state mesh domain. Linearized mesh domain is highlighted.

Grahic Jump Location
Fig. 4

100% speed-line. Design point is highlighted.

Grahic Jump Location
Fig. 5

Different number of master nodes (above). MAC of reduced real modes when compared to the full real modes (below).

Grahic Jump Location
Fig. 6

19 GAMs from axial (X) displacement of master nodes. Absolute amplitudes. Eliminated modes are highlighted.

Grahic Jump Location
Fig. 7

19 Least square error when fitting the 11 X and Z arbitrary modes to the real modes (above). Matched modes (below).

Grahic Jump Location
Fig. 8

Aerodynamic damping from the first seven real modes using the MLS general method. Zoomed-in view of mode 1.

Grahic Jump Location
Fig. 9

Stability from arbitrary modes oscillated at f1

Grahic Jump Location
Fig. 10

SCA (top) and mean (bottom) and its differences with the real modes. Arbitrary modes are oscillated at f1.

Grahic Jump Location
Fig. 11

SCA (top) and mean (bottom) and its differences with the real modes. Arbitrary modes are oscillated at f7.

Grahic Jump Location
Fig. 12

Stability from arbitrary modes are oscillated at f4

Grahic Jump Location
Fig. 13

SCA (top) and mean (bottom) and its differences with the real modes. Arbitrary modes are oscillated at f4.

Grahic Jump Location
Fig. 14

SCA (top) and mean (bottom) and its differences with the real modes. Arbitrary modes are oscillated at f1 and f4.

Grahic Jump Location
Fig. 15

SCA (top) and mean (bottom) and its differences with the real modes. Arbitrary modes are oscillated at f4 and f7.

Grahic Jump Location
Fig. 16

Generalized real (left) and imaginary (right) forces of the 1st mode at different frequencies. Influence coefficient domain; MLS GAMs frequency fit (dashed lines).

Grahic Jump Location
Fig. 17

Influence coefficient generalized forces of all of the GAMs at f1

Grahic Jump Location
Fig. 18

Imaginary pressure coefficient for the X modes 2–5. Influence of blade 0 on itself.

Grahic Jump Location
Fig. 19

Imaginary pressure coefficient for the mode 6 Z. Influence of blade 0.

Grahic Jump Location
Fig. 20

Static pressure versus imaginary Cp loading at 90% span. GAM 6Z influence of blade 0. Shock regions are highlighted.

Grahic Jump Location
Fig. 21

Steady versus unsteady loading at 90% span. GAM 6Z influence of blade 1. Shock regions are highlighted.

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