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| Hauptseite > Workflowsammlungen > Eingereichte Dokumente > Large-Scale Simulations of a Non-generic Helicopter Engine Nozzle and a Ducted Axial Fan > print |
| Hauptseite > Workflowsammlungen > Eingereichte Dokumente > Large-Scale Simulations of a Non-generic Helicopter Engine Nozzle and a Ducted Axial Fan > print |
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| 041 | _ | _ | |a English |
| 100 | 1 | _ | |a Cetin, Mehmet Onur |0 P:(DE-HGF)0 |b 0 |
| 245 | _ | _ | |a Large-Scale Simulations of a Non-generic Helicopter Engine Nozzle and a Ducted Axial Fan |
| 260 | _ | _ | |a Cham |c 2016 |b Springer International Publishing |
| 295 | 1 | 0 | |a High Performance Computing in Science and Engineering ´15 / Nagel, Wolfgang E. (Editor) ; Cham : Springer International Publishing, 2016, Chapter 25 ; ISBN: 978-3-319-24631-4 ; doi:10.1007/978-3-319-24633-8 |
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| 520 | _ | _ | |a Large-eddy simulations (LESs) of a helicopter engine jet and an axial fan are performed by using locally refined Cartesian hierarchical meshes. For the computations a high-fidelity, massively parallelized solver for compressible flow is used. To verify the numerical method, a coaxial hot round jet is computed and the results are compared to reference data. The analysis is complemented by a grid convergence study for both applications, i.e., for the helicopter engine jet and the axial fan. For the helicopter engine jet, additional computations have been performed for two different nozzle geometries, i.e., a simplified nozzle geometry that is consisting of a center body and divergent outer annular channel, and a complete engine nozzle geometry with 4 additional struts were used. The presence of the struts results in a different potential core break-down and turbulence intensity. Furthermore, for the axial fan configuration, computations have been performed at two different volume flow rates. The reduction of the volume flow rate results in an interaction of the tip-gap vortex with the neighboring blade which leads to a higher turbulent kinetic energy near and inside the tip-gap region. |
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