Date of Award
Doctor of Philosophy (PhD)
Mechanical and Aerospace Engineering
Turbomachines--Blades--Aerodynamics, Turbomachines--Blades--Fluid dynamics
Investigated are the effects of pressure side film cooling hole placement and configuration on the surface heat transfer characteristics of a transonic turbine squealer blade tip. Eight different blade tip arrangements are investigated, which are denoted C1, C2, C3, B1, B2, B3, B4, and 8D. Data are provided which include spatially-resolved and line-averaged distributions of heat transfer coefficient ratio and adiabatic film cooling effectiveness. The SS/TS/WT (supersonic/transonic/wind tunnel) blow down facility is employed with a transonic test section containing a five blade linear cascade. Spatially-resolved surface heat transfer characteristics are measured using transient infrared thermography, and an impulse response transient measurement technique. Results indicate that heat transfer coefficient and adiabatic film cooling effectiveness distributions vary significantly as film cooling hole placement and configuration are altered.
Collopy, Hallie, "Effects of pressure side film cooling hole placement and configuration on surface heat transfer characteristics of a transonic turbine squealer blade tip" (2023). Dissertations. 279.
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