AIRFOIL HAVING BUILT-UP SURFACE WITH EMBEDDED COOLING PASSAGE

摘要

A component in a gas turbine engine includes an airfoil (10A) extending radially outwardly from a platform (16A) associated with the airfoil (10A). The airfoil (10A) includes opposed pressure (20A) and suction (22A) sidewalis, which converge at a first location defined at a leading edge (24A) of the airfoil and at a second location defined at a trailing edge (26A) of the airfoil (10A) opposed from the leading edge (24A). The component includes a built-up surface (54) adjacent to the leading edge (24A) at an intersection between the pressure sidewall (20A) and the platform (16A), and at least one cooling passage (46a-46d) at least partially within the built-up surface (54) at the intersection between the pressure sidewall (20A) and the platform (16A). The at least one cooling passage (46a-46d) is in fluid communication with a main cooling channel (38) within the airfoil (10a) and has an outlet (52a-52d)at the platform (16A) for providing cooling fluid directly from the main cooling (38A) channel to the platform (16A).