Local measurements of the heat transfer coefficient and pressure coefficient were conducted on the tip and near tip region of a generic turbine blade in a five-blade linear cascade. Two tip clearance gaps were used: 1.6% and 2.8% chord. Data was obtained at a Reynolds number of 2.3 X 10(5) based oil exit velocity and chord. Three different tip geometries were investigated: A flat (plain) tip, a suction-side squealer and a cavity squealer The experiments reveal that the flow through the plain gap is dominated by flow separation at the pressure-side edge and that the highest levels of heat transfer are located where the flow, reattaches on the tip surface. High heat transfer is also measured at locations where the tip-leakage vortex has impinged onto the suction surface of the aerofoil. The experiments are supported by, flow visualization computed using the CFX CFD code which has provided insight into the fluid dynamics within the gap. The suction-side and cavity squealers are shown to reduce the heat transfer in the gap but high levels of heat transfer are associated with locations of impingement, identified using the floit, visualization and aerodynamic data. Film cooling is introduced oil the plain tip at locations near the pressure-side edge within the separated region and a net heat flux reduction analysis is used to quantify the performance of the successful cooling design.
|Number of pages||10|
|Journal||Journal of Turbomachinery: Transactions of the ASME|
|Publication status||Published - 2006|
|Event||ASME 50th International Gas Turbine and Aerospace Congress - Reno|
Duration: 1 Jun 2005 → …