Czestochowa University of Technology Areas of interest Energy and Aero Priorities 1.Mathematical modelling of flows in blade system of rotating machinery 2.Modelling of free flows, jets and wakes in aeronautical industry 3.Modelling of flow and electrochemical phenomena in fuel cells 4.Modelling of complex thermal systems in power engineering 5.Modelling of aerodynamics, heat and mass transfer in gas-solid particles flows 6.Renewable fuels combustion modeling of aeroengine combustor and aircraft wake/engine jet interactions (prof. A. Boguslawski) wall transitional flow modeling in aeroengine gas turbine bladings and turbulent boundary layer simulations (prof. W. Elsner). Institute of Thermal Machinery al. Armii Krajowej 21, Czestochowa, Poland

Czestochowa University of Technology MOLECULES (5 th FP) - Elaboration of modern software tools ( CFD ) for calculations and simulations of flows and combustion processes proceeding inside combustion chambers of aeroengines INTELLECT - 6 th Framework Programme of UE. Elaboration of numerical models of modern aeroengines TIMECOP-AE (6 th FP) – Toward Innovative Methods for Combustion Prediction in Aero-Engines Modeling of aeroengine combustion chamber Areas of interest - „Modeling of turbulent flows with combustion by Large Eddy Simulation in connection with Conditional Moment Closure model” Vrije Universiteit of Brussels - Czestochowa University of Technology Bilateral project COST Action P20 LES-AID Large-Eddy Simulation for Advanced Industrial Design

Czestochowa University of Technology Investigation of aeroengine aerodynamics TRANSPRETURB Thematic Network (5 th FP) – upgrading of current industrial CFD capabilities, defining requirements for further RTD model and transition model development UTAT (5 th FP) - Understanding of mechanisms of blade-row interactions as well as unsteady laminar-turbulent transition process in axial-flow turbines UTAT Aircraft aerodynamics FarWake (6 th FP) – interaction of vortices with airplane for Airbus WallTurb (6 th FP) – basic research on turbulent boundary layer affected by adverse pressure gradientfor Airbus WallTurb (6 th FP) – basic research on turbulent boundary layer affected by adverse pressure gradient for Airbus Areas of interest - „Turbulence and transition modelling methods in turbomachinery applications” Ghent University - Czestochowa University of Technology Bilateral project Areas of interest -

Czestochowa University of Technology Experimental Facilities, Equipment and Software  turbine bladings - rotor simulator  environmental aerodynamics  heated jets  countercurrent / heated jets open-loop wind tunnels Computational resources Software tools Fluent, GambitFluent, Gambit academic codes unNEWT+PUIM (Cambridge)unNEWT+PUIM (Cambridge) Sparc (Karlsruhe)Sparc (Karlsruhe) BOFFIN (Imperial College)BOFFIN (Imperial College) SAILOR (IMC Częstochowa)SAILOR (IMC Częstochowa) Procesor type: Dual-Core AMD Opteron 8214, Number of processors 8 (number of nodes 16) 32 GB RAM Procesor type: Dual-Core AMD Opteron 8222, Number of processors 8 (number of nodes 16), 64 GB RAM

Czestochowa University of Technology jet velocity 12.5 m/s spark on the jet axis: 10D, 30D, 40D, 50D spark radius 2.5 mm, Gaussian shape Spark ignition of the methane jet: BOFFIN-LES solver with Eulerian PDF method LES+PDFExperiment SPARK Animation 5

Czestochowa University of Technology Animation (successful ignition) Animations correspond to ignition at this location Animation (unsuccessful ignition) Modelling of the spray ignition: animations illustrating unsuccessful and successful ignition process SPARK 10mm SPARK 15 mm Initial spark temperature growth Spark is modelled by adding the source term in the enthalpy equation. 6

Czestochowa University of Technology Modelling of the spark ignition and light across using BOFFIN code Animation Spark  Due to extremely time consuming simulations for three sector configuration the spark parameters (location and size) are chosen such to guarantee successful ignition in selected sector.  Basing on previous experiments performed for single sector case the spark was located close to the edge of the recirculation zone, the size of the spark was equal to 15 mm.  Three-steps solution procedure: (cold flow  spray  ignition (flame propagation)) took more than 3 months, this corresponds to less than one second of real life ! View of the instantaneous axial velocity before ignition. Blue colour denotes negative velocity (recirculation zone). View of the instantaneous droplets distribution and spark kernel just after ignition. 7