The airfoil of a gas turbine and method for cooling a junction between the airfoil trailing edge and side wall of the gas turbine.

摘要

The invention relates to an airfoil (202) of a gas turbine, the gas turbine including: a first sidewall, an airfoil (202) positioned between the first sidewall (204) and a second sidewall (206), and a first channel in the airfoil in the vicinity a high temperature region, wherein the first channel is configured to receive a cooling fluid, wherein the high temperature region is proximate a junction between the first sidewall (204) and a trailing edge (212) of the airfoil (202). The turbine further includes a first diffuser (220) in flow communication with the first channel, the first diffuser (220) configured to direct the cooling fluid to form a film on a surface of the first sidewall (204).