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Simonsson, Kjell
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Publications (10 of 80) Show all publications
Andersson, H., Simonsson, K., Hilding, D., Schill, M. & Leidermark, D. (2017). System level co-simulation of a control valve and hydraulic cylinder circuit in a hydraulic percussion unit. In: Petter Krus, Liselott Ericson and Magnus Sethson (Ed.), Proceedings of 15:th Scandinavian International Conference on Fluid Power, June 7-9, 2017, Linköping, Sweden: . Paper presented at 15th Scandinavian International Conference on Fluid Power, June 7-9, 2017, Linköping, Sweden (pp. 225-235). Linköping: Linköping University Electronic Press, 144
Open this publication in new window or tab >>System level co-simulation of a control valve and hydraulic cylinder circuit in a hydraulic percussion unit
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2017 (English)In: Proceedings of 15:th Scandinavian International Conference on Fluid Power, June 7-9, 2017, Linköping, Sweden / [ed] Petter Krus, Liselott Ericson and Magnus Sethson, Linköping: Linköping University Electronic Press, 2017, Vol. 144, p. 225-235Conference paper, Published paper (Refereed)
Abstract [en]

In this study a previously developed co-simulation method that is based on a 1D system model representing the fluid components of a hydraulic machinery, within which structural 3D Finite Element (FE) models can be incorporated for detailed simulation of specific sub-models or complete structural assemblies, is further developed. The fluid system model consists of ordinary differential equation sub-models that are computationally very inexpensive, but still represents the fluid dynamics very well. The co-simulation method has been shown to work very well for a simple model representing a hydraulic driven machinery. A more complex model was set up in this work, in which two cylinders in the hydraulic circuit were evaluated. Such type of models, including both the main piston and control valves, are necessary as they represent the real application to a further extent than the simple model, of only one cylinder. Two models have been developed and evaluated, from the simple rigid body representation of the structural mechanics model, to the more complex model using linear elastic representation. The 3D FE-model facilitates evaluation of displacements, stresses, and strains on a local level of the model. The results can be utilised for fatigue assessment, wear analysis and for predictions of noise radiation.

Place, publisher, year, edition, pages
Linköping: Linköping University Electronic Press, 2017
Series
Linköping Electronic Conference Proceedings, ISSN 1650-3686, E-ISSN 1650-3740 ; 144
Keywords
Co-simulation, Fluid-structure coupling, System simulation, Functional mockup interface, Fluid power machinery, Transmission line modelling
National Category
Applied Mechanics Vehicle Engineering Control Engineering
Identifiers
urn:nbn:se:liu:diva-151015 (URN)10.3384/ecp17144225 (DOI)9789176853696 (ISBN)
Conference
15th Scandinavian International Conference on Fluid Power, June 7-9, 2017, Linköping, Sweden
Available from: 2018-09-11 Created: 2018-09-11 Last updated: 2018-09-11Bibliographically approved
Ewest, D., Almroth, P., Sjödin, B., Leidermark, D. & Simonsson, K. (2016). Comparison between linear and non-linear fracture mechanics analysis of experimental data for the ductile superalloy Haynes 230. Journal of engineering for gas turbines and power, 138(6), 062101-1-062101-7
Open this publication in new window or tab >>Comparison between linear and non-linear fracture mechanics analysis of experimental data for the ductile superalloy Haynes 230
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2016 (English)In: Journal of engineering for gas turbines and power, ISSN 0742-4795, E-ISSN 1528-8919, Vol. 138, no 6, p. 062101-1-062101-7Article in journal (Refereed) Published
Abstract [en]

With increasing use of renewable energy sources, an industrial gas turbine is often a competitive solution to balance the power grid. However, life robustness approaches for gas turbine components operating under increasingly cyclic conditions are a challenging task. Ductile superalloys, as Haynes 230, are often used in stationary gas turbine hot parts such as combustors. The main load for such components is due to nonhomogeneous thermal expansion within or between parts. As the material is ductile, there is considerable redistribution of stresses and strains due to inelastic deformations during the crack initiation phase. Therefore, the subsequent crack growth occurs through a material with significant residual stresses and strains. In this work, fatigue crack propagation experiments, including the initiation phase, have been performed on a single edge notched specimen under strain controlled conditions. The test results are compared to fracture mechanics analyses using the linear ΔK and the nonlinear ΔJ approaches, and an attempt to quantify the difference in terms of a life prediction is made. For the tested notched geometry, material, and strain ranges, the difference in the results using ΔKeff or ΔJeff is larger than the scatter seen when fitting the model to the experimental data. The largest differences can be found for short crack lengths, when the cyclic plastic work is the largest. The ΔJ approach clearly shows better agreement with the experimental results in this regime.

Place, publisher, year, edition, pages
ASME Press, 2016
National Category
Applied Mechanics Other Materials Engineering
Identifiers
urn:nbn:se:liu:diva-126576 (URN)10.1115/1.4031712 (DOI)000374713500010 ()
Note

Funding agencies: Siemens Industrial Turbomachinery AB, Finspang, Sweden

Available from: 2016-03-30 Created: 2016-03-30 Last updated: 2017-11-30
Kapidzic, Z., Ansell, H., Schön, J. & Simonsson, K. (2016). Fatigue bearing failure of CFRP composite in bolted joints exposed to biaxial variable amplitude loading at elevated temperature. Composite structures, 142, 71-77
Open this publication in new window or tab >>Fatigue bearing failure of CFRP composite in bolted joints exposed to biaxial variable amplitude loading at elevated temperature
2016 (English)In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 142, p. 71-77Article in journal (Refereed) Published
Abstract [en]

Hybrid structures than contain composite-aluminium interfaces tend to develop internal loads at elevated temperatures. In long bolted joints, the thermally induced bolt loads are superimposed onto the mechanically applied load and can induce a biaxial bearing load state. This paper presents an experimental and numerical study of the bearing fatigue failure of carbon-epoxy laminate specimens, exposed to uniaxial and biaxial variable amplitude loading at 90C. A specifically designed experimental rig was used, where both the mechanical and the thermally induced bolt loads were applied by means of mechanical load actuators. A fatigue model based on the kinetic theory of fracture for polymers, which was previously implemented for constant amplitude loading, is expanded to account for the variable amplitude load history. The results suggest that the biaxial loading gives a longer fatigue life than the uniaxial loading for the same maximum peak resultant force. This result can be utilized as a conservative dimensioning strategy by designing biaxially loaded joints in terms of maximum peak resultant bearing load using uniaxial fatigue data.

Place, publisher, year, edition, pages
Elsevier, 2016
Keywords
Carbon-epoxy, Thermally induced load, Fatigue bearing failure, Variable amplitude loading
National Category
Composite Science and Engineering
Identifiers
urn:nbn:se:liu:diva-122420 (URN)10.1016/j.compstruct.2016.01.064 (DOI)000372691300008 ()
Note

Vid tiden för disputation förelåg publikationen som manuskript

Funding agencies:  Swedish Armed Forces; Swedish Defence Materiel Administration; Swedish Governmental Agency for Innovation Systems

Available from: 2015-11-02 Created: 2015-11-02 Last updated: 2017-12-01Bibliographically approved
Storgärds, E., Saarimäki, J., Simonsson, K., Sjöström, S., Månsson, T. & Moverare, J. (2016). Influence of Superimposed Vibrational Load on Dwell Time Crack Growth in a Ni-Based Superalloy. International Journal of Fatigue, 87, 301-310
Open this publication in new window or tab >>Influence of Superimposed Vibrational Load on Dwell Time Crack Growth in a Ni-Based Superalloy
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2016 (English)In: International Journal of Fatigue, ISSN 0142-1123, E-ISSN 1879-3452, Vol. 87, p. 301-310Article in journal (Refereed) Published
Abstract [en]

Sustained loads have for some Ni-based superalloys been shown to give rise to increased crack growth rate at elevated temperature. Such loads generate a history dependent fatigue problem due to weakening and cracking of grain boundaries during dwell times, later broken apart during subsequent load cycles. So far most studies have focused on the interaction of load cycles, overloads, and temperature. However, vibrations of different kinds are to some extent always present in engine components, and an investigation of how such loads affect the dwell time cracking, and how to incorporate them in a modelling context, is therefore of importance. In this paper a study of the most frequently used gas turbine material, Inconel 718, has been carried out. Mechanical crack propagation testing has been conducted at 550 °C for surface cracks with and without the interaction of superimposed vibrational loads. Subsequent investigation of the fracture behaviour was performed by scanning electron microscopy and the modelling work has been conducted by incorporating the vibration load description within a history dependent crack growth law. The obtained results show reasonable accuracy with respect to the mechanical test results.

Place, publisher, year, edition, pages
Elsevier, 2016
Keywords
Dwell time, vibrational load, crack growth modelling, Inconel 718, high temperature
National Category
Applied Mechanics
Identifiers
urn:nbn:se:liu:diva-126921 (URN)10.1016/j.ijfatigue.2016.02.018 (DOI)000374615900032 ()
Note

Funding agencies:  Swedish Energy Agency; Siemens Industrial Turbomachinery AB; GKN Aerospace Engine Systems; Royal Institute of Technology through the Swedish research programme TURBO POWER

Available from: 2016-04-07 Created: 2016-04-07 Last updated: 2017-11-30
Storgärds, E., Simonsson, K., Sjöström, S., Gustafsson, D. & Månsson, T. (2016). Modeling of Crack Growth With Dwell Time for Aero-engine Spectra Loadings in a Ni-Based Superalloy. Journal of engineering for gas turbines and power, 138(1), 012501-012501
Open this publication in new window or tab >>Modeling of Crack Growth With Dwell Time for Aero-engine Spectra Loadings in a Ni-Based Superalloy
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2016 (English)In: Journal of engineering for gas turbines and power, ISSN 0742-4795, E-ISSN 1528-8919, Vol. 138, no 1, p. 012501-012501Article in journal (Refereed) Published
Abstract [en]

Testing and simulation of aero-engine spectra with dwell times are reported in this paper. The modeling concept used is built on linear elastic fracture mechanics (LEFM) and provides a history-dependent evolution description of dwell damage and its interaction with cyclic load. The simulations have been carried out for three spectra: (1) cyclic loads, (2) combined sustained load and cyclic loads, and (3) slow load ramps and cyclic loads, all for surface cracks at 550 °C for Inconel 718. All simulations show reasonable good agreement with experimental results. Prediction of multiple tests of several batches is also provided to show statistical scatter.

Place, publisher, year, edition, pages
ASME Press, 2016
National Category
Applied Mechanics Mechanical Engineering Materials Engineering
Identifiers
urn:nbn:se:liu:diva-121005 (URN)10.1115/1.4031155 (DOI)000371127900012 ()
Note

Funding agencies: Swedish Energy Agency; Siemens Industrial Turbomachinery AB; GKN Aerospace Engine Systems; Royal Institute of Technology through Swedish Research Programme TURBO POWER

Available from: 2015-09-02 Created: 2015-09-02 Last updated: 2017-12-04Bibliographically approved
Storgärds, E., Saarimäki, J., Simonsson, K., Sjöström, S., Gustafsson, D., Månsson, T. & Moverare, J. (2016). Scatter in Dwell Time Cracking for a Ni-Based Superalloy in Combination With Overloads. Journal of engineering for gas turbines and power, 138(1), 012502-012502
Open this publication in new window or tab >>Scatter in Dwell Time Cracking for a Ni-Based Superalloy in Combination With Overloads
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2016 (English)In: Journal of engineering for gas turbines and power, ISSN 0742-4795, E-ISSN 1528-8919, Vol. 138, no 1, p. 012502-012502Article in journal (Refereed) Published
Abstract [en]

In this paper, scatter in crack growth for dwell time loadings in combination with overloads has been investigated. Multiple tests were performed for surface cracks at 550 °C in the commonly used high temperature material Inconel 718. The test specimens originate from two different batches which also provide for a discussion of how material properties affect the dwell time damage and overload impact. In combination with these tests, an investigation of the microstructure was also carried out, which shows how it influences the growth rate. The results from this study show that, in order to take overloads into consideration when analyzing spectrum loadings containing dwell times, one needs a substantial amount of material data available as the scatter seen from one batch to the other are of significant proportions.

Place, publisher, year, edition, pages
ASME Press, 2016
National Category
Mechanical Engineering Materials Engineering Applied Mechanics
Identifiers
urn:nbn:se:liu:diva-121007 (URN)10.1115/1.4031157 (DOI)000371127900013 ()
Note

Funding agencies: Swedish Energy Agency; Siemens Industrial Turbomachinery AB; GKN Aerospace Engine Systems; Royal Institute of Technology through Swedish research programme TURBO POWER

Available from: 2015-09-02 Created: 2015-09-02 Last updated: 2017-12-04Bibliographically approved
Storgärds, E., Simonsson, K., Sjöström, S. & Moverare, J. (2016). Thermomechanical Fatigue Crack Growth Modeling in a Ni-Based Superalloy Subjected to Sustained Load. Journal of engineering for gas turbines and power, 138(1), 012503-012503
Open this publication in new window or tab >>Thermomechanical Fatigue Crack Growth Modeling in a Ni-Based Superalloy Subjected to Sustained Load
2016 (English)In: Journal of engineering for gas turbines and power, ISSN 0742-4795, E-ISSN 1528-8919, Vol. 138, no 1, p. 012503-012503Article in journal (Refereed) Published
Abstract [en]

Thermomechanical fatigue (TMF) crack growth modeling has been conducted on Inconel 718 with dwell time at maximum load. A history dependent damage model taking dwell damage into account, developed under isothermal conditions, has been extended for TMF conditions. Parameter determination for the model is carried out on isothermal load controlled tests at 550–650 °C for surface cracks, which later have been used to extrapolate parameters used for TMF crack growth. Further, validation of the developed model is conducted on a notched specimen subjected to strain control at 50–550 °C. Satisfying results are gained within reasonable scatter level compared for test and simulated number of cycles to failure.

Place, publisher, year, edition, pages
ASME Press, 2016
National Category
Mechanical Engineering Materials Engineering Applied Mechanics
Identifiers
urn:nbn:se:liu:diva-121008 (URN)10.1115/1.4031158 (DOI)000371127900014 ()
Note

Funding agencies: Swedish Energy Agency; Siemens Industrial Turbomachinery AB; GKN Aerospace Engine Systems; Royal Institute of Technology through Swedish research programme TURBO POWER

Available from: 2015-09-02 Created: 2015-09-02 Last updated: 2017-12-04Bibliographically approved
Storgärds, E., Simonsson, K. & Sjöström, S. (2016). Three-dimensional crack growth modelling of a Ni-based superalloy at elevated temperature and sustained loading. Theoretical and applied fracture mechanics (Print)
Open this publication in new window or tab >>Three-dimensional crack growth modelling of a Ni-based superalloy at elevated temperature and sustained loading
2016 (English)In: Theoretical and applied fracture mechanics (Print), ISSN 0167-8442, E-ISSN 1872-7638Article in journal (Refereed) Published
Abstract [en]

High temperature materials subjected to elevated temperature have been shown to be sensitive to dwell times, giving an increased crack growth rate. The interaction between these dwell times and rapid cyclic loads have been shown to constitute a complex problem. Many models have been developed for 1D conditions, but the application to general 3D conditions has seldom been seen, although this is the most common case in most structures. In this paper a model for taking care of the interaction between these load modes in general 3D crack growth has been developed. The model uses 1D results for extension to general 3D, thus providing for local crack front evolution with a minimum of numerical simulations. The model has been implemented for usage with finite element calculations and several different tests are simulated and compared with experimental results for the nickel based superalloy Inconel 718 at 550◦C. The simulation results show crack shapes in agreement with experimental fracture surfaces and time to failure.

Keywords
Sustained load, Crack growth modelling, Crack tunnelling, Ni-based superalloy, High temperature
National Category
Applied Mechanics Materials Engineering
Identifiers
urn:nbn:se:liu:diva-121004 (URN)10.1016/j.tafmec.2015.11.008 (DOI)000369204600002 ()
Note

Funding agencies:  Swedish Energy Agency; Siemens Industrial Turbomachinery AB; GKN Aerospace Engine Systems; Royal Institute of Technology through the Swedish research programme TURBO POWER

Vid tiden för disputation förelåg publikationen som manuskript

Available from: 2015-09-02 Created: 2015-09-02 Last updated: 2017-12-04Bibliographically approved
Busse, C., Gustafsson, D., Rasmusson, P., Sjodin, B., Moverare, J., Simonsson, K. & Leidermark, D. (2016). Three-Dimensional LEFM Prediction of Fatigue Crack Propagation in a Gas Turbine Disk Material at Component Near Conditions. Journal of engineering for gas turbines and power, 138(4), Article ID 042506.
Open this publication in new window or tab >>Three-Dimensional LEFM Prediction of Fatigue Crack Propagation in a Gas Turbine Disk Material at Component Near Conditions
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2016 (English)In: Journal of engineering for gas turbines and power, ISSN 0742-4795, E-ISSN 1528-8919, Vol. 138, no 4, article id 042506Article in journal (Refereed) Published
Abstract [en]

In this paper, the possibility to use linear elastic fracture mechanics (LEFM), with and without a superimposed residual stress field, to predict fatigue crack propagation in the gas turbine disk material Inconel 718 has been studied. A temperature of 400 degrees C and applied strain ranges corresponding to component near conditions have been considered. A three-dimensional crack propagation software was used for determining the stress intensity factors (SIFs) along the crack path. In the first approach, a linear elastic material behavior was used when analyzing the material response. The second approach extracts the residual stresses from an uncracked model with perfectly plastic material behavior after one loading cycle. As a benchmark, the investigated methods are compared to experimental tests, where the cyclic lifetimes were calculated by an integration of Paris law. When comparing the results, it can be concluded that the investigated approaches give good results, at least for longer cracks, even though plastic flow was taking place in the specimen. The pure linear elastic simulation overestimates the crack growth for all crack lengths and gives conservative results over all considered crack lengths. Noteworthy with this work is that the 3D-crack propagation could be predicted with the two considered methods in an LEFM context, although plastic flow was present in the specimens during the experiments.

Place, publisher, year, edition, pages
ASME, 2016
National Category
Mechanical Engineering
Identifiers
urn:nbn:se:liu:diva-126240 (URN)10.1115/1.4031526 (DOI)000371125800020 ()
Note

Funding Agencies|Siemens Industrial Turbomachinery AB through Research Consortium of Materials Technology for Thermal Energy Processes [KME-702]; Swedish Energy Agency

Available from: 2016-03-21 Created: 2016-03-21 Last updated: 2017-11-30
Ewest, D., Almroth, P., Sjodin, B., Leidermark, D. & Simonsson, K. (2015). COMPARISON BETWEEN LINEAR AND NON-LINEAR FRACTURE MECHANICS ANALYSIS OF EXPERIMENTAL DATA FOR THE DUCTILE SUPERALLOY HAYNES 230. In: PROCEEDINGS OF THE ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 7A: . Paper presented at ASME Turbo Expo: Turbine Technical Conference and Exposition. ASME Press (V07AT28A014)
Open this publication in new window or tab >>COMPARISON BETWEEN LINEAR AND NON-LINEAR FRACTURE MECHANICS ANALYSIS OF EXPERIMENTAL DATA FOR THE DUCTILE SUPERALLOY HAYNES 230
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2015 (English)In: PROCEEDINGS OF THE ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2015, VOL 7A, ASME Press, 2015, no V07AT28A014Conference paper, Published paper (Refereed)
Abstract [en]

Vith increasing use of renewable energy sources, an industrial us turbine is often a competitive solution to balance the power rid. However, life robustness approaches for gas turbine corn9nents operating under increasingly cyclic conditions, is a chalmging task. Ductile superalloys, as Haynes 230, are often used n stationary gas turbine hot parts such as combustors. The main cad for such components is due to non -homogeneous thermal xpansion within or between parts. As the material is ductile Jere is considerable redistribution of stresses and strains due to nelastic deformations during the crack initiation phase. There ore, the subsequent crack growth occurs through a material with :gnificant residual stresses and strains. In this work, fatigue ack propagation experiments, including the initiation phase, ave been performed on a single edge notched specimen under train controlled conditions. The test results are compared to -acture mechanics analyses using the linear AK and the non near AJ approaches, and an attempt to quantify the difference 2 terms of a life prediction is made. For the tested notched gemetry, material and strain ranges, the difference in the results using AKeff or ATeff are larger than the scatter seen when fitting the model to the experimental data. The largest differences can be found for short crack lengths, when the cyclic plastic work is the largest. The AJ approach clearly shows better agreement with the experimental results in this regime.

Place, publisher, year, edition, pages
ASME Press, 2015
National Category
Other Materials Engineering
Identifiers
urn:nbn:se:liu:diva-129512 (URN)10.1115/GT2015-43380 (DOI)000375810700024 ()978-0-7918-5676-5 (ISBN)
Conference
ASME Turbo Expo: Turbine Technical Conference and Exposition
Available from: 2016-06-20 Created: 2016-06-20 Last updated: 2016-06-20
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