A transient calorimeter technique for determining regional heat transfer coefficients in the three-temperature flowfield at a turbine airfoil leading edge by Nowlin, SR, Gillespie, D, Ireland, P, Knoche, R, Kingston, T, ASME

The effects of combustor cooling features on nozzle guide vane film cooling experiments by Holgate, N, Ireland, P, Romero, E

“…It is found that dilution port injection can create significant effectiveness benefits at the difficult-to-cool vane stagnation region due to the more turbulent hot mainstream enhancing the mixing of film coolant jets that have left the airfoil surface.</p> <br/> <p>Also explored are the implications of endwall film cooling for infrared vane surface temperature measurements. …”

Blade tip heat transfer and aerodynamics in a large scale turbine cascade with moving endwall by Palafox, P, Oldfield, M, Ireland, P, Jones, T, LaGraff, J, ASME

“…Analysis of pressure measurements on the blade airfoil surface and tip surface along with PIV velocity flow fields in the gap give an understanding of the heat transfer mechanism. …”

Blade Tip Heat Transfer and Aerodynamics in a Large Scale Turbine Cascade With Moving Endwall by Palafox, P, Oldfield, M, Ireland, P, Jones, T, LaGraff, J

“…Analysis of pressure measurements on the blade airfoil surface and tip surface along with particle image velocimetry velocity flow fields in the gap gives an understanding of the heat transfer mechanism. © 2012 American Society of Mechanical Engineers.…”

An experimental and computational parametric investigation of flow conditions in intersecting circular passages by Nowlin, SR, Gillespie, D, Ireland, P, Romero, E, Mitchell, M, ASME

“…In some industrial applications such as turbine airfoil film cooling, coolant passage configurations must maintain sufficient pressure margin to prevent hot gas ingestion whilst using holes of large enough diameter to avoid foreign object blockage. …”