01 0

Figure 2a-b. Non-dimensional temperature (a) and pressure (b) measurements upstream of the turbine vane with cooling from the combustor film-cooling holes.

Figure 3. Measured adiabatic effectiveness levels on the turbine endwall downstream of the combustor liner film-cooling holes for a coolant flow of 1% of the core flow.

Figure 4. Contours of eta for cases (a) 1% slot cooling, uniform inlet (b) 2% slot cooling, uniform inlet (c) 1% slot cooling, inlet profile.

Figure 5. Non-dimensional temperature contours for 1% slot cooling with an inlet temperature profile.
Figure 6. Pathlines colored by non-dimensional spanwise velocity for a case with no slot and a uniform temperature profile.
0 0

Post a comment