Modern design of turbine blades usually requires highly loaded, very thin profiles in order to save weight and cost. If local leading edge incidence is kept close to zero, then flow separation might occur on the pressure side. Although it is known that flow separation, flow reattachment, and the associated zones of recirculation have a major impact on the heat transfer to the wall, the turbomachinery community needs an understanding of the heat transfer mechanisms in separated flows as well as models and correlations to predict them. The aim of the present investigation is a detailed study by means of an in-house CFD code, $MU2S2T,$ of the heat transfer mechanisms in separated flows, in particular in separation and reattachment point regions. Furthermore, an attempt is made to identify a limited number of parameters (i.e., Re, M, inlet flow angle, etc.) whose influence on the heat flux would be critical. The identification of these parameters would be the starting point to develop special correlations to estimate the heat transfer in separated flow regions.

1.
Bassi, F., Rebay, S., Savini, M., Colantuoni, S., and Santoriello, G. “A Navier-Stokes Solver With Different Turbulence Models Applied to Film-Cooled Turbine Cascades,” Heat Transfer and Cooling in Gas Turbines, AGARD-CP-527, 1993.
2.
Rivir
,
R. B.
,
Johnston
,
J. P.
, and
Eaton
,
J. K.
,
1997
, “
Heat Transfer on a Flat Surface Under a Region of Turbulent Separation
,”
ASME J. Turbomach.
,
116
(
1
), pp.
57
62
.
3.
Bellows
,
R. J.
, and
Mayle
,
R. E.
,
1986
, “
Heat Transfer Downstream of a Leading Edge Separation Bubble
,”
ASME J. Turbomach.
,
108
(
3
), pp.
131
136
.
4.
Wolf, S., Homeier, L., and Fottner, L., 2001, “Experimental Investigation of Heat Transfer in Separated Flow on a Highly Loaded LP Turbine Cascade,” Proc. RTO/AVT Symposium and Specialists Meeting Heat Transfer and Cooling in Propulsion and Power Systems, Loen, Norway, May 7–11.
5.
Merzkirch
,
W.
,
Page
,
R. H.
, and
Fletcher
,
L. S.
,
1988
, “
A Survey of Heat Transfer in Compressible Separated and Reattached Flows
,”
AIAA J.
,
26
(
2
), pp.
144
150
.
6.
Hoheisel, H., 1990, “Test Case E/CA-6, Subsonic Turbine Cascade T106,” Test Cases for Computation of Internal Flows in Aero Engine Components, AGARD-AR-275, July.
7.
Arts, T., and Lambert de Rouvroit, M., 1990, “Aero-Thermal Performance of a Two Dimensional Highly Loaded Transonic Turbine Nozzle Guide Vane,” Gas Turbine and Aeroengine Congress and Exposition, Brussels, Belgium, June 11–14.
8.
Corral, R., and Fernandez-Castan˜eda, J., 1998, “Surface Mesh Generation by Means of Steiner Triangulation,” AIAA-98-3013, presented at 29th AIAA Fluid Dynamics Conference, Albuquerque, NM, June 15–18.
9.
Wilcox
,
D. C.
,
1988
, “
Reassessment of the Scale Determining Equation for Advanced Turbulence Models
,”
AIAA J.
,
26
, pp.
1299
1310
.
10.
Corral, R., and Contreras, J., 2000, “Quantitative Influence of the Steady Non-Reflecting Boundary Conditions on Blade-to-Blade Computations,” presented at 45th ASME Gas Turbine and Aeroengine Congress, Exposition and Users Symposium, Munich, May 8–11.
11.
Jameson
,
A.
,
Schmidt
,
W.
, and
Turkel
,
E.
, 1981, “Numerical Solution of the Euler Equations by Finite Volume Method using Runge-Kutta Time Stepping Schemes,” AIAA Pap., 81–1259.
12.
Gehrer
,
A.
, and
Jericha
,
H.
, 1999, “External Heat Transfer Predictions in a Highly Loaded Transonic Linear Turbine Guide Vane Cascade Using and Upwind Biased Navier-Stokes Solver,” ASME J. Turbomach., 121(3).
13.
Boyle
,
R. J.
, and
Ameri
,
A. A.
, 1997, “Grid Orthogonality Effects on Predicted Turbine Midspan Heat Transfer and Performance,” ASME J. Turbomach., 119(1).
14.
Hall
,
E. J.
, and
Pletcher
,
J. D.
,
1985
, “
Application of a Viscous-Inviscid Procedure to Predict Separated Flows with Heat Transfer
,”
ASME J. Heat Transfer
,
107
(
3
), pp.
557
563
.