Abstract Highly resolved large-eddy simulations (LES) of a helicopter engine jet including the nozzle geometry are performed. A flow solver for compressible flow based on hierarchically refined Cartesian meshes and a conservative cut-cell method is used for the computations. The impact of the nozzle geometry on the jet development is analyzed for two variants of the nozzle geometry, a simplified geometry with only a center body and the full geometry of the engine nozzle including four struts which support the center body. A synthetic turbulence formulation is used to prescribe inlet boundary conditions for the nozzle, which mimic the exit conditions after the last turbine stage. To verify the numerical method, a single cold round jet is computed and the results are compared to reference data. Results for the helicopter engine jet are presented for the time-averaged velocity field and turbulence intensities.
Investigation of the Effect of a Realistic Nozzle Geometry on the Jet Development
Proceedings of the 5th International Conference on Jets, Wakes and Separated Flows (ICJWSF2015) ; 6 ; 399-405
Springer Proceedings in Physics ; 185 , 6
2016-01-01
7 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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