fm m t f

cases of interest. In general, the objectives for the work presented Downlthe liner produces highly nonuniform temperature and pressure radial profiles as it exits the combustor and enters into the turbine. These nonuniformities typically span 10–15 % of the inner and outer radii at the platforms of the first vane. In addition, most combustor-turbine interfaces include, depending on the design, a backward-facing slot, a forward-facing slot, or a flush slot through which coolant leaks into the main gas path. The interaction be-tween the liner and slot flows as well as interaction with the highly turbulent mainstream, which is produced from combustor dilution holes, dictates the total pressure profile coming in to the passage of the first vane. In turn, this total pressure profile in the near-platform region dictates the development of the secondary flow through the vane passage. Moreover, these secondary flows dictate the heat transfer to the platform of the first vane and the exit flow angles for the rotor. To improve the understanding of this complex flow, highly-resolved measurements were taken using a combined large-scale combustor simulator and first vane. The combustor simulator in-cludes large dilution holes, film-cooling holes along the approach-ing liner, and a backward-facing slot at the combustor-turbine interface. Although this simulator does not include the effects of combustion, these studies were directed at understanding the ef-fects of representative combustor flow fields on the secondary in this paper were the following: i! to evaluate the effect of vari-ous liner flows on the exit total pressure profiles and ii! to quantify adiabatic wall temperatures as a function of different liner cooling flows and different slot flows. Summary of Past Literature Many past studies have led to a range of secondary flow models in turbine airfoil passages. Secondary flows refer to velocity com-ponents not aligned with the inviscid flow through the passage. Driving the secondary flows are two pressure gradients: the inher-ent pressure gradient from turning the flow and the pressure gra-dient resulting from nonuniform inlet conditions along the radial span of the airfoil passage. Langsto