Hostname: page-component-78c5997874-m6dg7 Total loading time: 0 Render date: 2024-11-14T13:20:57.019Z Has data issue: false hasContentIssue false
  • English
  • Français

Analysis of mistuned forced response in an axial high-pressure compressor rig with focus on Tyler–Sofrin modes

Published online by Cambridge University Press:  05 April 2019

F. Figaschewsky ,
A. Kühhorn ,
B. Beirow ,
T. Giersch  and
S. Schrape
F. Figaschewsky*
Affiliation:
Brandenburg University of Technology Cottbus–Senftenberg, Cottbus, Germany
A. Kühhorn
Affiliation:
Brandenburg University of Technology Cottbus–Senftenberg, Cottbus, Germany
B. Beirow
Affiliation:
Brandenburg University of Technology Cottbus–Senftenberg, Cottbus, Germany
T. Giersch
Affiliation:
Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow, Germany
S. Schrape
Affiliation:
Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow, Germany
*
*[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper aims at contributing to a better understanding of the effect of Tyler–Sofrin Modes (TSMs) on forced vibration responses by analysing a 4.5-stage research axial compressor rig. The first part starts with a brief review of the involved physical mechanisms and necessary prerequisites for the generation of TSMs in multistage engines. This review is supported by unsteady CFD simulations of a quasi 2D section of the studied engine. It is shown that the amplitude increasing effect due to mistuning can be further amplified by the presence of TSMs. Furthermore, the sensitivity with respect to the structural coupling of the blades and the damping as well as the shape of the expected envelope is analysed.

The second part deals with the Rotor 2 blisk of the research compressor rig. The resonance of a higher blade mode with the engine order of the upstream stator is studied in two different flow conditions realised by different variable stator vane (VSV) schedules which allows to separate the influence of TSMs from the impact of mistuning. A subset of nominal system modes representation of the rotor is used to describe its mistuned vibration behaviour, and unsteady CFD simulations are used to characterise the present strength of the TSMs in the particular operating conditions. Measured maximum amplitude vs blade pattern and frequency response functions are compared against the predictions of the aeromechanical models in order to assess the strength of the TSMs as well as its influence on vibration levels.

Keywords

MistuningForced responseTyler–Sofrin modes
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1261 , March 2019 , pp. 356 - 377
Copyright
© Royal Aeronautical Society 2019 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Castanier, M.P. and Pierre, C. Modeling and analysis of mistuned bladed disk vibration: status and emerging directions, Journal of Propulsion and Power, 2006, 22, (2), pp 384–396.Google Scholar
2. Whitehead, D.S. Effect of mistuning on the vibration of turbomachine blades induced by wakes, Journal of Mechanical Engineering Science, 1966, 8, (1), pp 15–21.Google Scholar
3. Kielb, R. and Kaza, K. Effects of structural coupling on mistuned cascade flutter and response, Journal of Engineering for Gas Turbines and Power, 1984, 106, (1), pp 17–24.Google Scholar
4. Hoyniak, D. and Fleeter, S. The effect of circumferential aerodynamic detuning on coupled bending-torsion unstalled supersonic Flutter, Journal of Turbomachinery, 1986, 108, (2), pp 253–260.Google Scholar
5. Martel, C., Corral, R. and Llorens, J. M. Stability Increase of aerodynamically unstable rotors using intentional mistuning, Journal of Turbomachinery, 2008, 130, (1), pp 011006.Google Scholar
6. Yang, M.-T. and Griffin, J.H. A reduced-order model of mistuning using a subset of nominal modes, ASME J of Engineering for Gas Turbines and Power, 2001, 123, (October), pp 893–900.Google Scholar
7. Giersch, T., Hönisch, P., Beirow, B. and Kühhorn, A. Forced response analyses of mistuned radial inflow turbines, Journal of Turbomachinery, 2013, 135, (3), pp 031034.Google Scholar
8. Tyler, J.M. and Sofrin, T.G. Axial flow compressor noise studies, Society of Automotive Engineers Transactions, 1962, 70, (1), pp 309–332.Google Scholar
9. Schrape, S., Giersch, T., Nipkau, J., Stapelfeldt, S. and Mück, B. Tyler-Sofrin Modes In Axial High Pressure Compressor Forced Response Analyses. In Proceedings of the 14th International Symposium on Unsteady Aerodynamics, Aeroacoustics & Aeroelasticity of Turbomachines(ISUAAAT), 2015.Google Scholar
10. Schoenenborn, H. Analysis of the Effect of Multi-Row and Multi-Passage Aerodynamic Interaction on the Forced Response Variation in a Compressor Configuration: Part 1—Aerodynamic Excitation. In Proceedings of the ASME Turbo Expo 2017: Paper GT2017-63018, 2017.Google Scholar
11. Gross, J., Krack, M. and Schoenenborn, H. Analysis of the Effect of Multi-Row and Multi-Passage Aerodynamic Interaction on the Forced Response Variation in a Compressor Configuration: Part 2—Effects of Additional Structural Mistuning. In Proceedings of the ASME Turbo Expo 2017: Paper GT2017-63019, 2017.Google Scholar
12. Beirow, B., Kühhorn, A., Figaschewsky, F., Hönisch, P., Giersch, T. and Schrape, S. Model Update and Validation of a Mistuned High Pressure Compressor Blisk. In Proceedings of the 23nd International Conference on Air Breathing Engines: Paper ISABE-2017-22568, 2017. ISABE.Google Scholar
13. Besem, F., Kielb, R. and Key, N. Forced Response Sensitivity of a Mistuned Rotor From an Embedded Compressor Stage. In Proceedings of the ASME Turbo Expo 2015: Paper GT2015-43032, 2015.Google Scholar
14. Figaschewsky, F., Kühhorn, A., Beirow, B., Nipkau, J., Giersch, T. and Power, B. Design and Analysis of an Intentional Mistuning Experiment Reducing Flutter Susceptibility and Minimizing Forced Response of a Jet Engine Fan. In Proceedings of the ASME Turbo Expo 2017: Paper GT2017-64621, 2017.Google Scholar
15. Johann, E., Mueck, B. and Nipkau, J. Experimental and Numerical Flutter Investigation of the 1st Stage Rotor in 4-Stage High Speed Compressor. In Proceedings of the ASME Turbo Expo 2008: Paper GT2008-50698, 2008.Google Scholar
16. Roeber, T., Kuegeler, E. and Weber, A. Investigation of Unsteady Flow Effects in an Axial Compressor Based on Whole Annulus Computations. In Proceedings of the ASME Turbo Expo 2010: Paper GT2010-23522, 2010.Google Scholar
17. Sayma, A.I., Vahdati, M. and Imregun, M. An integrated nonlinear approach for turbomachinery forced response prediction-Part 1: Formulation, Journal of Fluid and Structures, 2000, 14, (1), pp 87–101.Google Scholar
18. Vahdati, M, Sayma, A.I. and Imregun, M. An integrated nonlinear approach for turbomachinery forced response prediction-Part 2: Case Studies, Journal of Fluid and Structures, 2000, 14, (1), pp 103–125.Google Scholar
19. Sbardella, L., Sayma, A. and Imregun, M. Semi-unstructured meshes for axial turbomachine blades, Int J Numer Methods Fluids, 2000, 32, (5), pp 569–584.Google Scholar
20. Stelldinger, M., Giersch, T., Figaschewsky, F. and Kühhorn, A. A Semi-Unstructured Turbomachinery Meshing Library With Focus on Modeling of Specific Geometrical Features. In Proceedings of ECCOMAS VII European Congress on Computational Methods in Applied Sciences and Engineering, 2017.Google Scholar
21. 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. In Proceedings of the ASME Turbo Expo 2016: Paper GT2016-56458, 2016.Google Scholar