@article{KuehhornKlaukeGolze, author = {K{\"u}hhorn, Arnold and Klauke, Thomas and Golze, Mark}, title = {Simulation und Verifikation der sukzessiven Bruchabfolge eines CFK-Bauteils mittels neuartiger Bruchkriterien}, language = {de} } @article{KuehhornBeirowKlaukeetal., author = {K{\"u}hhorn, Arnold and Beirow, Bernd and Klauke, Thomas and Golze, Mark}, title = {Simulation der Mistuningeffekte von Hochdruckverdichter-Schaufelscheiben zur Bestimmung kritischer Schwingungen in Flugtriebwerken}, language = {de} } @inproceedings{KlaukeBeirowKuehhorn, author = {Klauke, Thomas and Beirow, Bernd and K{\"u}hhorn, Arnold}, title = {Experimental and numerical investigations of blade mistuning and strain gauge application effects in aero engine development}, language = {en} } @inproceedings{BeirowKuehhornGolzeetal., author = {Beirow, Bernd and K{\"u}hhorn, Arnold and Golze, Mark and Klauke, Thomas}, title = {Strukturdynamische Untersuchungen an Hochdruckverdichterschaufelscheiben unter Ber{\"u}cksichtigung von Mistuningeffekten}, series = {Modalanalyse und Identifikation, Verfahren und Anwendungen bei dynamischen Systemen, Tagung Wiesloch, 25. und 26. Mai 2004}, booktitle = {Modalanalyse und Identifikation, Verfahren und Anwendungen bei dynamischen Systemen, Tagung Wiesloch, 25. und 26. Mai 2004}, publisher = {VDI-Verlag}, address = {D{\"u}sseldorf}, isbn = {3-18-091825-X}, pages = {351 -- 372}, language = {de} } @inproceedings{KlaukeKuehhornBeirow, author = {Klauke, Thomas and K{\"u}hhorn, Arnold and Beirow, Bernd}, title = {Numerische Untersuchung des Schwingverhaltens von Hochdruckverdichter-Blisks mit fertigungsbedingten Anweichungen}, language = {de} } @inproceedings{KlaukeKuehhornLiangetal., author = {Klauke, Thomas and K{\"u}hhorn, Arnold and Liang, Luo and Kober, Markus}, title = {Entwicklung eines 3-Blatt-CFK-Verstellpropellers f{\"u}r Ultraleichtflugzeuge}, abstract = {Internationale AVK-Tagung, 13.-14. September 2010, Essen}, language = {de} } @inproceedings{KlaukeKuehhornLiangetal., author = {Klauke, Thomas and K{\"u}hhorn, Arnold and Liang, Luo and Kober, Markus and Sieghart, D. and F{\"u}hrer, M. and Viehweger, Bernd and Fritzsche, Christoph and Sarradj, Ennes}, title = {Entwicklung eines 3-Blatt-CFK-Verstellpropellers f{\"u}r Ultraleichtflugzeuge}, abstract = {Deutscher Luft- und Raumfahrkongress 2010, 31.08. - 02.09.2010, Hamburg}, language = {de} } @inproceedings{KlaukeKuehhornKober, author = {Klauke, Thomas and K{\"u}hhorn, Arnold and Kober, Markus}, title = {Application of a Newer Inter-Fiber-Failure Criteria on CFRPs in Aero Engine Development}, language = {en} } @inproceedings{BeirowKuehhornKlauke, author = {Beirow, Bernd and K{\"u}hhorn, Arnold and Klauke, Thomas}, title = {Lokalisierungsph{\"a}nomen bei Hochdruckverdichterschaufelscheiben}, language = {de} } @article{KuehhornBeirowKlauke, author = {K{\"u}hhorn, Arnold and Beirow, Bernd and Klauke, Thomas}, title = {Theoretische und experimentelle Untersuchungen von Schaufelschwingungen bei Verdichterintegralr{\"a}dern}, language = {de} } @inproceedings{KoberKuehhornKlauke, author = {Kober, Markus and K{\"u}hhorn, Arnold and Klauke, Thomas}, title = {Auslegung einer Flanschverbindung aus faserverst{\"a}rktem Kunststoff durch Optimierung der Faserorientierungen und Schichtdicken mit Hilfe von Altair HyperStudy unter Verwendung eines Wirkebenenbruchkriteriums als Nebenbedingung}, language = {de} } @inproceedings{KlaukeKuehhornBeirow, author = {Klauke, Thomas and K{\"u}hhorn, Arnold and Beirow, Bernd}, title = {Blade Mistuning Induced Blisk Vibration}, series = {1st CEAS European Air and Space Conference 2007, Deutscher Luft- und Raumfahrtkongress 2007, 10 - 13 September 2007, Berlin, Germany, Bd. 1}, booktitle = {1st CEAS European Air and Space Conference 2007, Deutscher Luft- und Raumfahrtkongress 2007, 10 - 13 September 2007, Berlin, Germany, Bd. 1}, publisher = {Dt. Ges. f{\"u}r Luft- und Raumfahrt}, address = {Bonn}, pages = {335 -- 345}, language = {en} } @inproceedings{KoberKlaukeKuehhornetal., author = {Kober, Markus and Klauke, Thomas and K{\"u}hhorn, Arnold and Lenk, Olaf}, title = {Einbindung eines modernen Wirkebenenbruchkriteriums f{\"u}r faserverst{\"a}rkte Kunststoffe in eine Parameteroptimierung mit Altair HyperStudy}, language = {de} } @inproceedings{KoberKuehhornKlaukeetal., author = {Kober, Markus and K{\"u}hhorn, Arnold and Klauke, Thomas and Lenk, Olaf}, title = {Topology-Optimized Intermediate Casing of Aero Engine and Comparative Evaluation of Titanium and Composite Architecture in Terms of Load Capacity and Weight Reduction}, series = {Proceedings of the ASME Turbo Expo 2008, presented at the 2008 ASME Turbo Expo, June 9 - 13, 2008, Berlin, Germany, Vol. 5, part A}, booktitle = {Proceedings of the ASME Turbo Expo 2008, presented at the 2008 ASME Turbo Expo, June 9 - 13, 2008, Berlin, Germany, Vol. 5, part A}, publisher = {ASME}, address = {New York, NY}, isbn = {978-0-7918-4315-4}, pages = {69 -- 79}, language = {en} } @inproceedings{KlaukeKuehhornBeirowetal., author = {Klauke, Thomas and K{\"u}hhorn, Arnold and Beirow, Bernd and Parchem, Roland}, title = {Blade Vibration Phenomena of HPC Bliscs Considering Manufacturing Effects and Strain Gauge Application}, series = {Proceedings of the ASME Turbo Expo 2008, presented at the 2008 ASME Turbo Expo, June 9 - 13, 2008, Berlin, Germany, Vol. 5, part A}, booktitle = {Proceedings of the ASME Turbo Expo 2008, presented at the 2008 ASME Turbo Expo, June 9 - 13, 2008, Berlin, Germany, Vol. 5, part A}, publisher = {ASME}, address = {New York, NY}, isbn = {978-0-7918-4315-4}, pages = {403 -- 413}, language = {en} } @misc{KlaukeStrehlauKuehhorn, author = {Klauke, Thomas and Strehlau, Ulrik and K{\"u}hhorn, Arnold}, title = {Integer Frequency Veering of Mistuned Blade Integrated Disks}, series = {Journal of Turbomachinery}, volume = {135}, journal = {Journal of Turbomachinery}, number = {6}, issn = {1528-8900}, doi = {10.1115/1.4024022}, pages = {061004-1 -- 061004-7}, abstract = {As a result of more balanced blade aspect ratios of modern blade-integrated disks (blisks), interactions between disk-dominated and blade-dominated modes are becoming more and more important, especially if blade mistuning is considered. The specific vibration behavior in these transition regions is characterized by a mix of both fundamental mode types into "coupled" modes. In this paper, numerical and experimental investigations based on a front high-pressure compressor (HPC) blisk stage were carried out in order to determine the effect of blade mistuning on those regions in detail. At this, effects like mode localization and amplitude magnification are found to be weakened in an integer frequency-veering zone. Contrary to this, blisks are very sensitive to mistuning in regions of pure blade-dominated mode families with high modal density.}, language = {en} } @misc{GambittaBeirowKlauke, author = {Gambitta, Marco and Beirow, Bernd and Klauke, Thomas}, title = {Investigation of Rear Blisk Drum Dynamics Under Consideration of Multi-Stage Coupling}, series = {ASME Journal of Engineering for Gas Turbines and Power}, volume = {146}, journal = {ASME Journal of Engineering for Gas Turbines and Power}, number = {2}, doi = {10.1115/1.4063633}, pages = {8}, abstract = {The analysis of the structural dynamics of multistage cyclic structures as linked components is required to model the interstage coupling. In turbomachinery, this can result in a collaboration between different compressor or turbine stages. This paper investigates the coupling between two rear drum blade integrated disk stages of an axial compressor to support the mechanical design process. Considering the vibration modeshapes of a multistage system, different components may coparticipate in the dynamics. For this reason, criteria to identify the modes affected by the coupling and to quantify this coupling are defined. This allows to distinguish between modes with interstage coupling, requiring the multistage system for their description, and uncoupled modes, involving a single stage. In addition, it is of interest to research methods to reduce the impact of the coupling on the vibrating system without drastically altering the geometry of the components. The vibration analyses of a two-stage compressor generalized geometry, representative of a compressor rear drum blisk, are presented as a study case. The use of a reducing method allows to describe the behavior of the nominal multistage system with a computationally efficient technique, enabling a parametric analysis of the stages' coupling. The investigation considers the effect of a set of geometrical and mechanical parameters on the dynamics, identifying the driving parameters of the coupled vibration characteristics.}, language = {en} } @inproceedings{BeirowKuehhornGolzeetal., author = {Beirow, Bernd and K{\"u}hhorn, Arnold and Golze, Mark and Klauke, Thomas}, title = {Experimentelle Untersuchungen des strukturdynamischen Verhaltens von Hochdruckverdichterschaufeln in Integralbauweise (Blisks) mittels Laser-Doppler-Vibrometrie}, language = {de} } @phdthesis{Klauke, author = {Klauke, Thomas}, title = {Schaufelschwingungen integraler, realer Verdichterr{\"a}der im Hinblick auf Verstimmung und Lokalisierung}, url = {http://nbn-resolving.de/urn:nbn:de:kobv:co1-opus-4081}, language = {de} } @misc{WeberKuehhornKlaukeetal., author = {Weber, Robby and K{\"u}hhorn, Arnold and Klauke, Thomas and Schrape, Sven}, title = {The Effect of Sand Erosion on a Compressor Blade and its Modal Properties}, series = {Proceedings of ASME Turbo Expo 2020, Turbomachinery Technical Conference and Exposition, GT2020, September 21-25, 2020, Virtual, Online}, journal = {Proceedings of ASME Turbo Expo 2020, Turbomachinery Technical Conference and Exposition, GT2020, September 21-25, 2020, Virtual, Online}, pages = {9}, abstract = {The wear and damage of High-Pressure Compressor (HPC) blades due to erosion or Foreign Object Damage (FOD) have a significant influence on HPC aerodynamic performance, vibration resistance against High-Cycle Fatigue (HCF) and thus component lifetime. The changes in airfoil geometry reduce the overall engine efficiency. Furthermore extended off-wing engine maintenances due to blade failures are increasing the cost of ownership. The safe operation of every engine within a reduced number of shop visits requires a reliable prediction of future deterioration. This enables the optimization of services and off-wing time. One contribution to this is a better understanding of the component's dynamics and based on this providing an improved wear modeling to reliably predict the remaining lifetime and the decreased efficiency. This contribution determines the material removal of HPC blades due to sand erosion. Originally, this stage was built as a blisk (Blade Integrated Disk). After sand erosion test completion, the blisk was cut into segments containing one airfoil only. First, the material removal is determined for ten blades of one exemplary rotor. A blue light fringe projector is employed to identify the geometrical differences between the eroded blades and the nominal design. Second, realistic finite element models are generated to enable comparable modal analyses of eroded blades. This procedure suffers from unavoidable and mostly random imperfections due to the manufacturing process, which significantly affects the blade surface before the erosion test can be conducted. Therefore, an already published approach is implemented in the third step to predict the blade surface after erosion based on nominal blade design. The investigation is completed by comparing measured and predicted surfaces. Finally, the aforementioned tool is employed to predict the locations and intensities of the material losses and the accompanying change in modal properties of this compressor blade concerning operational time.}, language = {de} } @inproceedings{KlaukeKuehhornGolzeetal., author = {Klauke, Thomas and K{\"u}hhorn, Arnold and Golze, Mark and Villwock, J. and Lenk, Olaf}, title = {Finite-Elemente-Anwendung neuerer Faserverbund-Bruchkriterien und deren Verifizierung mittels CFK-Bauteilpr{\"u}fung}, series = {Deutscher Luft- und Raumfahrtkongress 2003, M{\"u}nchen, 17. bis 20. November 2003, Bd. 1}, booktitle = {Deutscher Luft- und Raumfahrtkongress 2003, M{\"u}nchen, 17. bis 20. November 2003, Bd. 1}, publisher = {Dt. Ges. f{\"u}r Luft- und Raumfahrt}, address = {Bonn}, pages = {113 -- 120}, language = {de} } @misc{KlaukeKuehhornBeirowetal., author = {Klauke, Thomas and K{\"u}hhorn, Arnold and Beirow, Bernd and Golze, Mark}, title = {Numerical Investigations of Localized Vibrations of Mistuned Blade Integrated Disks (Blisks)}, language = {de} } @misc{GambittaBeirowKlauke, author = {Gambitta, Marco and Beirow, Bernd and Klauke, Thomas}, title = {Investigation of Rear Blisk Drum Dynamics Under Consideration of Multi-Stage Coupling}, series = {Proceedings of ASME Turbo Expo 2023, Boston, Massachusetts, June 26-30, 2023}, journal = {Proceedings of ASME Turbo Expo 2023, Boston, Massachusetts, June 26-30, 2023}, isbn = {978-0-7918-8705-9}, doi = {10.1115/GT2023-103756}, abstract = {The analysis of the structural dynamics of multistage cyclic structures as linked components is required to model the interstage coupling. In turbomachinery, this can result in a collaboration between different compressor or turbine stages. This paper investigates the coupling between two rear drum blade integrated disk stages of an axial compressor to support the mechanical design process. Considering the vibration modeshapes of a multistage system, different components may co-participate in the dynamics. For this reason, a criteria to identify the modes affected by the coupling and to quantify this coupling is defined. This allows to distinguish between modes with inter-stage coupling, requiring the multistage system for their description, and uncoupled modes, involving a single stage. In addition, it is of interest to research methods to reduce the impact of the coupling on the vibrating system without drastically altering the geometry of the components. The vibration analyses of a two-stage compressor generalized geometry, representative of a compressor rear drum blisk, is presented as a study case. The use of a reducing method allows to describe the behavior of the nominal multistage system with a computationally efficient technique, enabling a parametric analysis of the stages' coupling. The investigation considers the effect of a set of geometrical and mechanical parameters on the dynamics, identifying the driving parameters of the coupled vibration characteristics.}, language = {en} } @inproceedings{KuehhornBeirowParchemetal., author = {K{\"u}hhorn, Arnold and Beirow, Bernd and Parchem, Roland and Klauke, Thomas}, title = {Schaufelschwingungen bei realen Verdichter-Integralr{\"a}dern (BLISK)}, series = {Deutscher Luft- und Raumfahrtkongress 2006, Braunschweig, 06. bis 09. November 2006, Bd. 2}, booktitle = {Deutscher Luft- und Raumfahrtkongress 2006, Braunschweig, 06. bis 09. November 2006, Bd. 2}, publisher = {Dt. Ges. f{\"u}r Luft- und Raumfahrt}, address = {Bonn}, pages = {1199 -- 1208}, language = {de} } @misc{HanschkeKlaukeKuehhorn, author = {Hanschke, Benjamin and Klauke, Thomas and K{\"u}hhorn, Arnold}, title = {The Effect of Foreign Object Damage on Compressor Blade High Cycle Fatigue Strength}, series = {ASME Turbo Expo 2017, GT2017-63559, June 26-30, 2017, Charlotte, NC, USA, Volume 7A}, journal = {ASME Turbo Expo 2017, GT2017-63559, June 26-30, 2017, Charlotte, NC, USA, Volume 7A}, publisher = {ASME}, address = {New York, NY}, isbn = {978-0-7918-5092-3}, doi = {10.1115/GT2017-63599}, pages = {9}, abstract = {For a considerable amount of time blade integrated disks (blisks) are established as a standard component of high pressure compressors (HPCs) in aero engines. Due to the steady requirement to increase the efficiency of modern HPCs, blade profiles get thinned out and aerodynamic stage loading increases. Ever since, aerofoil design has to balance structural and aerodynamic requirements. One particularity of aero engines is the possibility to ingest different kinds of debris during operation and some of those particles are hard enough to seriously damage the aerofoil. Lately, a growing number of blisk-equipped aero engines entered service and the question of foreign object damage (FOD) sensitivity relating to compressor blade high cycle fatigue (HCF) has emerged. Correct prediction of fatigue strength drop due to a FOD provides a huge chance for cost cutting in the service sector as on-wing repairs (e.g. borescope blending) are much more convenient than the replacement of whole blisks and corresponding engine strips. The aim of this paper is to identify critical FOD-areas of a modern HPC stage and to analyze the effects of stress concentrations — caused by FOD — on the fatigue strength. A process chain has been developed, that automatically creates damaged geometries, meshes the parts and analyses the fatigue strength. Amplitude frequency strength (af-strength) has been chosen as fatigue strength indicator owing to the fact, that amplitudes and frequencies of blade vibrations are commonly measured either by blade tip timing or strain gauges. Furthermore, static and dynamic stress concentrations in damaged geometries compared to the reference design were computed. A random variation of input parameters was performed, such as the radial damage position at blade leading edge and damage diameter. Based on results of the different samples, correlations of input parameters and the fatigue strength drop have been investigated. Evaluation shows a significant mode dependence of critical blade areas with a large scatter between drops in fatigue strength visible for mode to mode comparison. Keeping in mind the necessity of fast response times in the in-service sector, FOD sensitivity computations could be performed for all blade rows of the HPC — including the analysis of possible borescope blending geometries — in the design stage. Finally, the actual amplitude frequency levels (af-levels) of the modes excited during operation have to be appropriately taken into consideration. For example, a pronounced af-strength drop due to a FOD may not be critical for safe engine operations because the observed mode is excited by small af-levels during operation. Hence, the endurance ratio — a quotient of af-level and af-strength — is used as assessment criterion. Copyright © 2017 by ASME}, language = {en} } @inproceedings{GerkeMaurerKlaukeetal., author = {Gerke, Horst H. and Maurer, Thomas and Klauke, A. and Dominik, R. and Dimitrov, M. and Biemelt, Detlef and Badorreck, Annika}, title = {Modelling the initial 3D sediment structure of an artificially constructed hydrological catchment}, series = {EGU General Assembly 2008, Wien}, booktitle = {EGU General Assembly 2008, Wien}, publisher = {European Geophysical Society}, address = {Katlenburg-Lindau}, language = {en} } @misc{GerkeMaurerDuseketal., author = {Gerke, Horst H. and Maurer, Thomas and Dusek, J. and Klauke, A. and Badorreck, Annika}, title = {A 3D structural model of a lignitic mine soil based on classification and interpolation of profile images}, series = {EUROSOIL 2008, Book of Abstracts, 25.-29. August 2008, Vienna, Austria}, journal = {EUROSOIL 2008, Book of Abstracts, 25.-29. August 2008, Vienna, Austria}, editor = {Blum, Winfried E. H. and Gerzabek, Martin H. and Vodrazka, Martin}, publisher = {University of Natural Resources and Applied Life Sciences (BOKU)}, address = {Wien}, isbn = {978-3-902382-05-4}, pages = {S. 175}, language = {en} }