  Flow past a low pressure turbine blade in a cascade at $Re \approx 52000$ and
angle of incidence $\alpha = 45.5^{0}$ is solved using a code developed
in-house for solving 3D compressible Navier-Stokes equations. This code, named
ANUROOP, has been developed in the finite volume framework using kinetic energy
preserving second order central differencing scheme for calculating fluxes, and
is compatible with hybrid grids. ANUROOP was verified and validated against
several test cases with Mach numbers ranging from 0.1 (Taylor-Green vortex) to
1.5 (compressible turbulent channel flow). The code was found to be robust and
stable, and the kinetic energy decay obeys the compressible Navier-Stokes
equations.
  A hybrid grid, with a high resolution hexahedral orthogonal mesh in the
boundary layer and unstructured (also hexahedral) elements in the rest of the
domain, is used for the turbine blade simulation. Total grid size (160 million)
is approximately an order of magnitude higher than in previous simulations for
the same flow conditions and using similar numerical methods. The discrepancy
in the pressure distribution in earlier studies compared to experimental data
has been removed in this simulation. The trailing edge separation bubble has
been characterized and a detailed discussion on the effect of surface curvature
is presented.
