Abstract: Ascertaining the uncertainty in the aerothermal performance of blade tips is crucial, as it represents the most delicate component of modern gas turbines. In this research article, a novel and efficient approach is proposed ...

Abstract: The uncertainty quantification in the turbine components' aerodynamic and heat transfer performances is widely considered to be the most challenging topic due to its intricate and nonlinear characteristics. This paper first ...

Abstract: The turbine vanes being manufactured and assembled piece by piece leads to an unavoidable gap on the vane endwall called slashface. Usually, the coolant leakage introduced from the slashface with a single surface angle ...

Abstract: Although the thermal-barrier coating (TBC) can protect the gas turbine components from the hot mainstream gas, it is not uncommon that the TBC partially blocks the film cooling holes during the spraying process. The film ...

Abstract: The ever-increasing combustor exit temperature in modern turbine engine designs raises cooling challenges for the nozzle guide vane (NGV). Due to the complexity of NGV cooling design, the cooling effect from the upstream ...

Abstract: This paper presents an experimental and computational study on implementing a dual cavity slashface cooling scheme on the thermal performance for the first stage nozzle guide vane with an axisymmetric, converging endwall. ...