Patent ID: 9022726
Filing Date: 2015-05-05
Classification: F01D,F05D,Y02T

Abstract:
1. A turbine blade configured to be thermally loaded and coupled to a cooling system configured to receive a gaseous cooling medium introduced in a forced manner from outside the turbine blade that flows through the cooling system so as to absorb and transport heat away from the turbine blade as a result of thermal contact with the turbine blade, the turbine blade comprising: at least one Helmholtz resonator configured to improve thermal contact between the cooling medium and the turbine blade, the at least one Helmholtz resonator including an enclosure having a constricted entrance; wherein the turbine blade includes a cooled blade airfoil including an interior through which the gaseous cooling medium flows, and wherein the at least one Helmholtz resonator is disposed in the interior of the blade airfoil; and wherein the blade airfoil includes a plurality of cooling passages extending in parallel in a radial direction, and wherein the Helmholtz resonators are integrated into the cooling passages.