A hybrid Large Eddy Simulation (LES) related technique is used to explore some key turbomachinery relevant flows. Near wall RANS modeling is used to cover over especially small scales, the LES resolution of which is generally intractable with current computational power. Away from walls, large eddy type simulation is used but with no LES model (NLES). Linking of the two model zones through a Hamilton-Jacobi equation is explored. The hybrid strategy is used to predict turbine and compressor endwall flows, flow around a fan blade section, jet flows and a cutback trailing edge. Also, application of NLES to the flow in an idealized high pressure compressor drum cavity is considered. Generally, encouraging results are found. However, challenges remain, especially for flows where transition modeling is important.

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