Erik Dick was born on December10, 1950 in Torhout, Belgium. He obtained a M.Sc. in Mechanical Engineering from Ghent University (Belgium) in 1973 and a Ph.D. in Computational Fluid Dynamics from the same university in 1980. From 1973 to 1991, he worked at Ghent University as researcher, senior researcher and head of research in the turbomachinery division of the Department of Mechanical Engineering. He became associate professor of thermal turbomachines and propulsion at the University of Liège (Belgium), in July 1991. He returned to Ghent University in September 1992 as associate professor and became full professor in 1995, with teaching in turbomachines and computational fluid dynamics. He retired in September 2014 and is now part-time individual senior researcher, combined with retirement. His area of research is computational methods and models of turbulence and transition for flow problems in mechanical engineering. He is author or co-author of about 130 papers in international scientific journals and about 220 papers at international scientific conferences. He is the author of a course book on Turbomachines, published in 2015 by Springer. He is the recipient of the 1990 Iwan Akerman award for fluid machinery of the Belgian National Science Foundation and he is the recipient of the 2002 Belgian Francqui Chair with a lecture series on simulation and modelling of complex flows at the University of Liège.
International Journal of Heat and Fluid Flow, Dec 1, 2016
Abstract An algebraic model using the intermittency concept is proposed for laminar to turbulent ... more Abstract An algebraic model using the intermittency concept is proposed for laminar to turbulent transition in attached and separated boundary layers. The model modifies the production terms of the k – ω RANS turbulence model by Wilcox. For attached flows, the model describes bypass transition by taking into account two main effects, which are damping of high-frequency disturbances by a laminar shear layer and breakdown of a near-wall laminar layer perturbed by streaks. For separated flow, the model describes breakdown of a laminar free shear layer. The proposed model is a modified and extended version of an earlier model by the authors for bypass transition only (Kubacki and Dick, Int. J. Heat and Fluid Flow, 58, 68–83, 2016). The primary tuning of the model has been done with flat plate T3C flows of ERCOFTAC with steady approaching flow, relevant for bypass transition and separation-induced transition. Secondary tuning has been done with two cascades with steady approaching flow at high turbulence level, one with N3-60 (Re = 6 × 10 5 ) steam turbine stator vanes and one with V103 (Re = 1.385 × 10 5 ) compressor blades. Model validation has been done for steady approaching flows of the same cascades, but including a case with low level of free-stream turbulence, and for a cascade with T106A (Re = 1.6 × 10 5 ) gas turbine rotor blades for high and low levels of free-stream turbulence. Further validation has been done for flow perturbed by travelling wakes through a cascade of N3-60 vanes at high and low levels of background turbulence level. The transition model produces good results for all cases, both for bypass transition in attached boundary layer state and for transition in separated boundary layer state.
International Journal of Heat and Fluid Flow, Apr 1, 2016
Abstract A simple algebraic model is proposed for laminar to turbulent transition in boundary lay... more Abstract A simple algebraic model is proposed for laminar to turbulent transition in boundary layers subjected to elevated free-stream turbulence. The model is combined with the newest version of the k - ω RANS turbulence model by Wilcox. The transition model takes into account, in an approximate way, two effects: filtering of high-frequency free-stream disturbances by shear and breakdown of near-wall disturbances into fine-scale turbulence. The model only uses local variables.The model has been tuned for the flat plate T3C cases of ERCOFTAC, relevant for bypass transition and tested for flow through cascades of N3-60 (Re = 6·10 5 ) steam turbine stator vanes, V103 (Re = 1.385·10 5 ) compressor blades and T106A (Re = 1.6·10 5 ) gas turbine rotor blades. The transition model produces good results for bypass transition in attached boundary layer state and in separated boundary layer state for flows of elevated free-stream turbulence, both for 2D steady RANS and 3D time-accurate RANS simulations. Good results are also obtained for transition in separated laminar boundary layers at low free-stream turbulence by 3D time-accurate RANS simulations, thanks to resolution of the boundary layer instability and the beginning of the breakdown of the generated spanwise vortices.
International Journal of Heat and Fluid Flow, Dec 1, 2016
Abstract An algebraic model using the intermittency concept is proposed for laminar to turbulent ... more Abstract An algebraic model using the intermittency concept is proposed for laminar to turbulent transition in attached and separated boundary layers. The model modifies the production terms of the k – ω RANS turbulence model by Wilcox. For attached flows, the model describes bypass transition by taking into account two main effects, which are damping of high-frequency disturbances by a laminar shear layer and breakdown of a near-wall laminar layer perturbed by streaks. For separated flow, the model describes breakdown of a laminar free shear layer. The proposed model is a modified and extended version of an earlier model by the authors for bypass transition only (Kubacki and Dick, Int. J. Heat and Fluid Flow, 58, 68–83, 2016). The primary tuning of the model has been done with flat plate T3C flows of ERCOFTAC with steady approaching flow, relevant for bypass transition and separation-induced transition. Secondary tuning has been done with two cascades with steady approaching flow at high turbulence level, one with N3-60 (Re = 6 × 10 5 ) steam turbine stator vanes and one with V103 (Re = 1.385 × 10 5 ) compressor blades. Model validation has been done for steady approaching flows of the same cascades, but including a case with low level of free-stream turbulence, and for a cascade with T106A (Re = 1.6 × 10 5 ) gas turbine rotor blades for high and low levels of free-stream turbulence. Further validation has been done for flow perturbed by travelling wakes through a cascade of N3-60 vanes at high and low levels of background turbulence level. The transition model produces good results for all cases, both for bypass transition in attached boundary layer state and for transition in separated boundary layer state.
International Journal of Heat and Fluid Flow, Apr 1, 2016
Abstract A simple algebraic model is proposed for laminar to turbulent transition in boundary lay... more Abstract A simple algebraic model is proposed for laminar to turbulent transition in boundary layers subjected to elevated free-stream turbulence. The model is combined with the newest version of the k - ω RANS turbulence model by Wilcox. The transition model takes into account, in an approximate way, two effects: filtering of high-frequency free-stream disturbances by shear and breakdown of near-wall disturbances into fine-scale turbulence. The model only uses local variables.The model has been tuned for the flat plate T3C cases of ERCOFTAC, relevant for bypass transition and tested for flow through cascades of N3-60 (Re = 6·10 5 ) steam turbine stator vanes, V103 (Re = 1.385·10 5 ) compressor blades and T106A (Re = 1.6·10 5 ) gas turbine rotor blades. The transition model produces good results for bypass transition in attached boundary layer state and in separated boundary layer state for flows of elevated free-stream turbulence, both for 2D steady RANS and 3D time-accurate RANS simulations. Good results are also obtained for transition in separated laminar boundary layers at low free-stream turbulence by 3D time-accurate RANS simulations, thanks to resolution of the boundary layer instability and the beginning of the breakdown of the generated spanwise vortices.
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Papers by Erik Dick