Abstract: A guide vane in a gas turbine engine includes an inner platform, an outer platform, and an airfoil extending therebetween. Side surfaces of the inner platform and outer platform between an adjacent guide vane define a first seal slot, a second seal slot, and a third seal slot forming a closed loop having three corners. At least one of the corners is rounded. The guide vane includes tubulator ribs and pin fins disposed in an airfoil interior. The pin fins are disposed in a region of the trailing edge. The inner platform defines film cooling holes disposed at an outer surface facing the airfoil. The film cooling holes are arranged in a fan shape. An inner surface of the inner platform and an outer surface of the outer platform include impingement cooling ribs. The inner platform protrudes further towards upstream in a flow direction than the outer platform.

Abstract: A guide vane in a gas turbine engine includes an inner platform, an outer platform, and an airfoil extending therebetween. Side surfaces of the inner platform and outer platform between an adjacent guide vane define a first seal slot, a second seal slot, and a third seal slot forming a closed loop having three corners. At least one of the corners is rounded. The guide vane includes tubulator ribs and pin fins disposed in an airfoil interior. The pin fins are disposed in a region of the trailing edge. The inner platform defines film cooling holes disposed at an outer surface facing the airfoil. The film cooling holes are arranged in a fan shape. An inner surface of the inner platform and an outer surface of the outer platform include impingement cooling ribs. The inner platform protrudes further towards upstream in a flow direction than the outer platform.

Abstract: An internally-cooled turbomachine component, having: a main body with a first end wall, a second end wall spaced apart from the first end wall, and a sidewall which extends between the first end wall and the second end wall such that the first end wall, the second end wall and the sidewall define a cooling passage extending between a fluid inlet and a fluid outlet, a pedestal bank with a plurality of pedestals which span the cooling passage between the first end wall and the second end wall, wherein the pedestal bank is spaced from the sidewall to define a flow channel therebetween; and a flow guide for directing cooling flow away from the flow channel, the flow guide extending from the flow channel into the pedestal bank.

Abstract: An internally-cooled turbomachine component, having: a main body with a first end wall, a second end wall spaced apart from the first end wall, and a sidewall which extends between the first end wall and the second end wall such that the first end wall, the second end wall and the sidewall define a cooling passage extending between a fluid inlet and a fluid outlet, a pedestal bank with a plurality of pedestals which span the cooling passage between the first end wall and the second end wall, wherein the pedestal bank is spaced from the sidewall to define a flow channel therebetween; and a flow guide for directing cooling flow away from the flow channel, the flow guide extending from the flow channel into the pedestal bank.