Abstract: A blade for a gas turbine engine includes an airfoil body. The airfoil body includes a pressure side wall, a suction side wall, and a tip end wall. The tip end wall forms a blade tip. The airfoil body forms a plurality of suction side wall passages and a main body cavity. The suction side wall includes an exterior wall segment and an interior wall segment. The suction side wall forms the plurality of suction side wall passages between the exterior wall segment and the interior wall segment. The interior wall segment and the exterior wall segment extend to the tip end wall. The plurality of suction side wall passages extend through the tip end wall to the blade tip. The interior wall segment and the pressure side wall form the main body cavity.

Abstract: A blade for a gas turbine engine includes an airfoil body. The airfoil body includes a pressure side wall, a suction side wall, and a tip end wall. The tip end wall forms a blade tip. The airfoil body forms a plurality of suction side wall passages and a main body cavity. The suction side wall includes an exterior wall segment and an interior wall segment. The suction side wall forms the plurality of suction side wall passages between the exterior wall segment and the interior wall segment. The interior wall segment and the exterior wall segment extend to the tip end wall. The plurality of suction side wall passages extend through the tip end wall to the blade tip. The interior wall segment and the pressure side wall form the main body cavity.

Abstract: A turbine engine airfoil element has: an airfoil having: an exterior surface including a pressure side and a suction side; and a plurality of spanwise passageways including: a plurality of main body passageways along a camber line; and a plurality of skin passageways between the main body passageways and the exterior surface, wherein; the skin passageways have: a downstream direction from one or more inlets; a skin side; first and second lateral rounded transitions from the skin side; a parting line; and a longitudinally spaced plurality of protrusions from the skin side; and the protrusions have a height profile having: first and second tapering portions tapering from a maximum height, the first and second portions extending downstream; and first and second inwardly concave transitions to the skin passageway lateral rounded transitions.

Abstract: A turbine engine airfoil element has: an airfoil having: an exterior surface including a pressure side and a suction side; and a plurality of spanwise passageways including: a plurality of main body passageways along a camber line; and a plurality of skin passageways between the main body passageways and the exterior surface, wherein; the skin passageways have: a downstream direction from one or more inlets; a skin side; first and second lateral rounded transitions from the skin side; a parting line; and a longitudinally spaced plurality of protrusions from the skin side; and the protrusions have a height profile having: first and second tapering portions tapering from a maximum height, the first and second portions extending downstream; and first and second inwardly concave transitions to the skin passageway lateral rounded transitions.

Abstract: A vane arc segment includes an airfoil fairing that has an airfoil wall that defines a fairing platform and a hollow airfoil section. A spar has a spar platform adjacent the fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg is spaced from the airfoil wall in the hollow airfoil section such that there is a first gap. The spar platform is spaced from the fairing platform such that there is a second gap. A support platform is secured to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform. There is a spring seal between the spar platform and the fairing platform. The spring seal biases the airfoil fairing toward the support platform and seals the first gap from the second gap.

Abstract: A vane arc segment includes an airfoil fairing that has an airfoil wall that defines a fairing platform and a hollow airfoil section. A spar has a spar platform adjacent the fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg is spaced from the airfoil wall in the hollow airfoil section such that there is a first gap. The spar platform is spaced from the fairing platform such that there is a second gap. A support platform is secured to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform. There is a spring seal between the spar platform and the fairing platform. The spring seal biases the airfoil fairing toward the support platform and seals the first gap from the second gap.