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Model update and validation of a mistuned high-pressure compressor blisk

Published online by Cambridge University Press:  14 March 2019

B. Beirow ,
A. Kühhorn ,
F. Figaschewsky ,
P. Hönisch ,
T. Giersch  and
S. Schrape
B. Beirow*
Affiliation:
Brandenburg University of Technology, Cottbus, Germany
A. Kühhorn
Affiliation:
Brandenburg University of Technology, Cottbus, Germany
F. Figaschewsky
Affiliation:
Brandenburg University of Technology, Cottbus, Germany
P. Hönisch
Affiliation:
ABB Turbo Systems, Baden, Switzerland
T. Giersch
Affiliation:
Rolls-Royce Deutschland, Blankenfelde-Mahlow, Germany
S. Schrape
Affiliation:
Rolls-Royce Deutschland, Blankenfelde-Mahlow, Germany
*
[email protected]
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Abstract

In order to prepare an advanced 4-stage high-pressure compressor rig test campaign, details regarding both accomplishment and analysis of preliminary experiments are provided in this paper. The superior objective of the research project is to contribute to a reliable but simultaneously less conservative design of future high pressure blade integrated disks (blisk). It is planned to achieve trend-setting advances based on a close combination of both numerical and experimental analyses. The analyses are focused on the second rotor of this research compressor, which is the only one being manufactured as blisk. The comprehensive test program is addressing both surge and forced response analyses e.g. caused by low engine order excitation. Among others the interaction of aeroelastics and blade mistuning is demanding attention in this regard. That is why structural models are needed, allowing for an accurate forced response prediction close to reality. Furthermore, these models are required to support the assessment of blade tip timing (BTT) data gathered in the rig tests and strain gauge (s/g) data as well. To gain the maximum information regarding the correlation between BTT data, s/g-data and pressure gauge data, every blade of the second stage rotor (28 blades) is applied with s/g. However, it is well known that s/g on blades can contribute additional mistuning that had to be considered upon updating structural models.

Due to the relevance of mistuning, efforts are made for its accurate experimental determination. Blade-by-blade impact tests according to a patented approach are used for this purpose. From the research point of view, it is most interesting to determine both the effect s/g-instrumentation and assembling the compressor stages on blade frequency mistuning. That is why experimental mistuning tests carried out immediately after manufacturing the blisk are repeated twice, namely, after s/g instrumentation and after assembling. To complete the pre-test program, the pure mechanical damping and modal damping ratios dependent on the ambient pressure are experimentally determined inside a pressure vessel. Subsequently the mistuning data gained before is used for updating subset of nominal system mode (SNM) models. Aerodynamic influence coefficients (AICs) are implemented to take aeroelastic interaction into account for forced response analyses. Within a comparison of different models, it is shown for the fundamental flap mode (1F) that the s/g instrumentation significantly affects the forced response, whereas the impact of assembling the compressor plays a minor role.

Keywords

BliskMistuningAerodynamic damping
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1260 , February 2019 , pp. 230 - 247
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Copyright
© Royal Aeronautical Society 2019 

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Footnotes

A version of this paper was presented at the ISABE 2017 Conference, 3–8 September 2017, Manchester, UK.

References

1. Srinivasan, A.V. Influence of mistuning on blade torsional flutter, R80-914545-16, United Technologies Research Center, East Hartford, Connecticut, US, 1980 (NASA CR-165137).Google Scholar
2. Whitehead, D.S. Effect of mistuning on the vibration of turbo-machine blades induced by wakes, J Mech Engineering Science, 1966, 8, pp 15–21.Google Scholar
3. Martel, C. and Corral, R. Asymptotic description of maximum mistuning amplification of bladed disk forced response, J Engineering Gas Turbines and Power, 2009, 131, pp 022506/1–022506/10.Google Scholar
4. Figaschwsky, F. and Kühhorn, A. Analysis of mistuned blade vibrations based on normally distributed blade individual natural frequencies, Proceedings of the ASME Turbo Expo 2015, GT2015-43121, 15–19 June 2015, Montréal, Canada.Google Scholar
5. Petrov, E.P. and Ewins, D.J. Analysis of the worst mistuning patterns in bladed disk assemblies, J Turbomachinery 2003, 125, pp 623–631.Google Scholar
6. Chan, Y.J. Variability of Blade Vibration in Mistuned Bladed Discs, PhD Dissertation, Imperial College, London, 2009.Google Scholar
7. Beirow, B., Kühhorn, A., Giersch, T. and Nipkau, J. Optimization-aided forced response analysis of a mistuned compressor blisk, J Enginerring Gas Turbines and Power, 2015, 137, (1), pp 012504/1–012504/10.Google Scholar
8. Chan, Y.J. and Ewins, D.J. The amplification of vibration response levels of mistuned bladed disks: its consequences and its distribution in specific situations, J Enginerring Gas Turbines and Power, 2011, 133, (10), pp 1–8.Google Scholar
9. Yang, M.T. and Griffin, Y.H. A reduced-order model of mistuning using a subset of nominal system modes, J Enginerring Gas Turbines and Power, 2001, 123, pp 893–900.Google Scholar
10. Figaschewsky, F., Kühhorn, A., Beirow, B., Schrape, S. and Giersch, T. Analysis of mistuned forced response in an axial high pressure compressor rig with focus on tyler-sofrin modes, Proceedings of ISABE 2017, Session 39, 22614, 7–10 September 2017, Manchester, UK. https://drive.google.com/uc?id=0B0DfCIh2pyLOeXVtazZBcUFEcVE&export=download.Google Scholar
11. Hanamura, Y., Tanaka, H. and Yamaguchi, K. A simplified method to measure unsteady forces acting on the vibrating blades in cascade, Bulletin of the JSME, 1980, 23, (180-12), pp 880–887.Google Scholar
12. Giersch, T., Hönisch, P., Beirow, B. and Kühhorn, A. Forced response analysis of mistuned radial inflow turbines, J Turbomachinery, 2013, 135, (3), pp 031034-1–031034-9.Google Scholar
13. Klauke, T., Kühhorn, A., Beirow, B. and Golze, M. Numerical investigations of localized vibrations of mistuned blade integrated disks (blisks), J Turbomachinery, 2009, 131, pp 031002-1–031002-11.Google Scholar
14. Kühhorn, A. and Beirow, B. Method for determining blade mistuning on integrally manufactured rotor wheels, Patent US 2010/0286934 A1, 2010.Google Scholar
15. Beirow, , , B., Kühhorn, A. and Nipkau, J. On the influence of strain gauge instrumentation on blade vibrations of integral blisk compressor rotors applying a discrete model, Proceedings of the ASME Turbo Expo 2009, GT2009-59207, 8–12 June 2009, Orlando, Florida, US.Google Scholar
16. Popig, F., Hönisch, P. and Kühhorn, A. Experimental and numerical analyses of geometrical induced mistuning, Proceedings of the ASME Turbo Expo 2015, GT2015-43272, 15–19 June 2015, Montréal, Canada.Google Scholar
17. Hönisch, P., Kühhorn, A. and Beirow, B. Experimental and numerical analyses of radial turbine blisks with regard to mistuning, Proceedings of the ASME Turbo Expo 2011, GT2011-45359, 6–10 June 2011, Vancouver, Canada.Google Scholar
18. Beirow, B., Maywald, T., Figaschewsky, F., Kühhorn, A., Heinrich, C.R. and Giersch, T. Simplified determination of aerodynamic damping for bladed rotors. Part 1: experimental validation at rest, Proceedings of the ASME Turbo Expo 2016, GT2016-56535, 13–17 June 2016, Seoul, South Korea.Google Scholar
19. Figaschewsky, F., Kühhorn, A., Beirow, B., Giersch, T., Nipkau, J. and Meinl, F. Simplified estimation of aerodynamic damping for bladed rotors. Part 2: experimental validation during operation, Proceedings of the ASME Turbo Expo 2016, GT2016-56458, 13–17 June 2016, Seoul, South Korea.Google Scholar
20. Klauke, T., Kühhorn, A., Beirow, B. and Parchem, R. Blade vibration phenomena of HPC bliscs considering manufacturing effects and strain gauge application, Proceedings of the ASME Turbo Expo 2008, GT2008-50683, 9–13 June 2008, Berlin, Germany.Google Scholar
21. Beirow, B., Kühhorn, A., Figaschewsky, F., Hönisch, P., Giersch, T. and Schrape, S. Model update and validation of a mistuned high pressure compressor blisk, Proceedings of ISABE 2017, ISABE-2017-22568, 2017, Manchester, UK. https://drive.google.com/uc?id=0B0DfCIh2pyLOeXVtazZBcUFEcVE&export=download.Google Scholar