Patent ID: 9151164
Filing Date: 2015-10-06
Classification: F01D,F05D,Y10T

Abstract:
1. A turbine vane segment of a vane ring of a gas turbine engine having a gaspath, said turbine vane segment comprising an airfoil disposed between a radially inner and a radially outer platform, said radially outer platform having a leading edge, a hollow platform leading edge core provided in said outer platform and extending along said leading edge, an air inlet port communicating with said platform leading edge air core to admit cooling air therein for cooling the leading edge of said radially outer platform, said airfoil having a hollow airfoil leading edge core extending along a leading edge portion thereof, an interconnecting passage provided between said platform leading edge core and a radially outer end portion of said airfoil leading edge core to channel the cooling air from said platform leading edge core to said airfoil leading edge core and creating a single cooling stream for cooling both said leading edge of said outer platform and said leading edge of said airfoil, wherein said radially outer platform has a band section disposed between a leading section and a trailing section; said leading edge of said outer platform being defined in a radially inner portion of said leading section, said air inlet port being located radially outwardly relative to said radially inner portion of said leading section and in communication with a cooling air stream; said platform leading edge core defining a leading edge cooling chamber disposed in said radially inner portion behind said leading edge of said radially outer platform, an inlet conduit in flow communication between said inlet port and an inlet end of said leading edge cooling chamber, and an outlet conduit at an outlet end of said leading edge cooling chamber in flow communication with said interconnecting passage.