Motivation and objectives
In modern aircraft engines blade integrated disks (Blisks) are used more and more, because they permit a high pressure ratio per stage while being lightweight. Due to their low mechanical damping, they are highly sensitive to vibration excitation. Geometrical variances caused by wear and regeneration have a significant influence on the vibrational behavior. The main goal is therefore the prediction of the operational vibrational behavior of multistage compressors, while considering these variances. The results enable accurate part life predictions.
Results
The current project results from the fusion of the sub-projects C6 “Aeroelasticity of Compressor Blisks” and C3 “Regeneration-induced Mistuning”. In the sub-project C6, the influence of (regeneration-induced) geometric variances on the vibrational behavior of an axial compressor blisk was analyzed, focusing on blend repairs. This influence was quantified in simulations, and shown in measurements using a blisk geometry designed for this purpose. The calculated aerodynamic damping was used in the sub-project C3 to enable more accurate simulations of the vibrational behavior. In this case, mistuning was focused – deviations from the cyclic symmetry. A model order reduction method developed earlier was extended to enable the consideration of deviations in the disk segments.
Current research and outlook
Currently there are two main goals: Extending the models to include multiple stages, and a direct integration of geometric variances into the reduced order model. In multi-stage models, the vibration excitation and response contain multiple harmonics which has to be considered. The stator angle of attack (of the stator vanes) is varied in order to realize this kind of excitation in the axial compressor (at TFD). In the end an integrated simulation method is developed that, together with the sub-projects B4 and C5, enables fast and accurate part life prediction for axial compressors. This represents an important contribution to the decision on the regeneration path.
Subproject leader
30823 Garbsen
30823 Garbsen
Staff
Publications
International Conference Paper, peer-reviewed
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(2017): Influence of Geometric Imperfections on Aerodynamic and Aeroelastic Behavior of a Compressor Blisk, In: Proceedings of ASME Turbo Expo 2017, Charlotte, USA, GT2017-63556
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(2017): Influence of Blade Repairs on Compressor Blisk Vibration considering Aerodynamic Damping and Mistuning, GPPS (Hg.): Proceedings of Global Power and Propulsion Society Conference. Shanghai
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(2017): Reduced Order Modeling of Mistuned Bladed Disks Considering Aerodynamic Coupling and Mode Family Interaction, In: Proceedings of 12th European Conference on Turbomachinery Fluid Dynamics & Thermodynamics (ETC12), April 3-7, Stockholm, Sweden, ETC2017-242
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(2016): An Acoustic Excitation System for the Generation of Turbomachinery Specific Sound Fields: Part II - Experimental Verification, In: Proceedings of the ASME Turbo Expo 2016, Seoul, South Korea
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(2016): An Acoustic Excitation System for the Generation of Turbomachinery Specific Sound Fields: Part I - Design and Methodology, In: Proceedings of the ASME Turbo Expo 2016, Seoul, South Korea
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(2015): Design Process of a 1.5-Stage Axial Compressor for Experimental Flutter Investigations, In: Proceedings of the International Gas Turbine Congress 2015, Tokyo, Japan, S. 1130–1139
International Conference Paper, not peer-reviewed
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(2018): Experimental Validation of a Forced Response Analysis Using a Time-Linearized Method, 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, AIAA SciTech Forum
DOI: 10.2514/6.2018-0461
National Conference Paper, not peer-reviewed
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(2020): Investigation of Multiharmonic Effects in a Single Stage High Speed Compressor, Deutscher Luft- und Raumfahrtkongress 2019, Darmstadt
DOI: 10.25967/490212
Books
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(2019): Advances in Production Management Systems. Towards Smart Production Management Systems, Springer International Publishing
ISBN: 978-3-030-29996-5
