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A DIRECT NUMERICAL SIMULATION OF FLOW THROUGH A LOW PRESSURE TURBINE STAGE
 

Summary: A DIRECT NUMERICAL SIMULATION OF FLOW THROUGH A
LOW PRESSURE TURBINE STAGE
Man Mohan Rai
AIAA-2011-3092
-objective: understand interaction between the stator wake and the
rotor blades (especially separation and transition)
-turbine/compressor flows are complex because of interaction
between blade rows.
-Low-pressure turbines (LPT) high Re at take-off, low Re at cruise
(50,000 500,000)
-At low Re, suction side tends to separate (leading to losses) and is
influenced by transition
-recently DNS has been used to compute moderate Re turbine and
compressor flows using supercomputers.
-All the boundary layers and wakes (stator and rotor) are computed
via DNS.
-only one stator blade and one rotor blade used with periodic
boundary conditions
-blades put in O-grids, inlet and outlet have rectangular grids
-rotor and outlet move relative to the stator and inlet

  

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

 

Collections: Engineering