Summary: 45th AIAA Aerospace Sciences Meeting and Exhibit, January 8­11, 2007/Reno, NV
Integrated RANS/LES Computations of an Entire
Gas Turbine Jet Engine
G. Medic
, G. Kalitzin
, D. You
, E. v. d. Weide§
, J. J. Alonso¶
, and H. Pitsch
Center for Turbulence Research & Aerospace Computing Lab
Stanford University, Stanford, CA
I. Introduction
The interaction between different components of a jet engine represents a very important aspect of
the engine design process. Sudden mass flow-rate changes induced by flow separation and pressure waves,
interaction of the unsteady wakes originating from the fan blades with the low-pressure compressor, high
temperature streaks interacting with the first stages of the turbine are all complex unsteady phenomena
that cannot be simply accounted for through boundary conditions of a single component simulation. Only
simulations that integrate multiple engine components can describe these flow features accurately.
Today's use of Computational Fluid Dynamics (CFD) in gas turbine design is usually limited to com-
ponent simulations. The demand on the models to represent the large variety of physical phenomena en-

Source: Alonso, Juan J. - Department of Aeronautics and Astronautics, Stanford University

Collections: Engineering