Abstract: An airfoil for use in a gas turbine engine is provided. The airfoil having: a pressure surface and a suction surface each extending axially from a leading edge to a trailing edge of the airfoil, at least one of the pressure surface, the suction surface, the leading edge and the trailing edge terminating at an edge of a tip section of the airfoil; a plurality of internal cooling channels located within the airfoil; and at least one cooling hole in fluid communication with at least one of the plurality of internal cooling channels, wherein the at least one cooling hole is aligned with an opening or diffuser that extends directly from the at least one cooling hole and wherein the opening or diffuser is formed in and extends through the edge of the tip section of the airfoil.

Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.

Abstract: An airfoil includes leading and trailing edges, a first exterior wall extending from the leading edge to the trailing edge and having inner and outer surfaces, a second exterior wall extending from the leading edge to the trailing edge generally opposite the first exterior wall and having inner and outer surfaces, and cavities within the airfoil. A first cavity extends along the inner surface of the first exterior wall and a first inner wall and has an upstream end and a downstream end, and a feed cavity is located between the first inner wall and the second exterior wall.

Abstract: A gas turbine engine airfoil includes a body that provides an exterior airfoil surface that extends in a radial direction to a tip. The exterior surface has a leading edge in a forward direction and a trailing edge in an aft direction. The tip includes a squealer pocket that has a recess surface. A cooling passage is arranged in the body. Each of the cooling holes extends from an inlet at the cooling passage to an outlet at the recessed surface. The inlet and outlet are arranged at an angle in an angular direction relative to the recessed surface. The angular direction is toward at least one of the forward and aft directions.

Abstract: A core assembly includes a core that includes an exterior surface that has a recessed area that extends along the exterior surface. An insert includes a contact surface that corresponds to the recessed area.

Abstract: An article for gas turbine engine includes a body that has a gaspath side for exposure in a core gaspath of a gas turbine engine. The gaspath side has an undulating surface. A cooling passage is in the body. The cooling passage has a undulating profile that corresponds to the undulating surface.

Abstract: The cooling system for a turbine may include a plurality of platform cooling openings positioned in a platform of the turbine airfoil. In particular, the first set of cooling openings may create a first cooling path and a second set of cooling openings may be placed in the path of the first cooling path where the first cooling flow will cool the second set of cooling openings.

Abstract: A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge.

Abstract: An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.

Abstract: An airfoil includes a pressure surface and a suction surface extending from a root section of the airfoil to a tip section of the airfoil. The airfoil also includes a leading edge and a trailing edge defining a chord length of the airfoil therebetween. The airfoil further includes a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall. The tip shelf wall is spaced between the pressure surface and the suction surface and the tip shelf extends from within 10% of the chord length measured from the leading edge to within 10% of the chord length measured from the trailing edge.

Abstract: A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.

Abstract: A turbomachine component includes a body defining a cooling inlet and a cooling outlet in fluid communication with each other through a cooling channel that defines a longitudinal axis, and at least one pedestal disposed within the cooling channel. The pedestal is angled within the cooling channel relative to the longitudinal axis. The turbomachine component can be a vane, a blade, a blade outer air seal, or a combustor panel.

Abstract: In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a reference plane extending in a spanwise direction along a surface of the internal wall, a first cavity and a second cavity separated by the internal wall, and a plurality of crossover passages within the internal wall and connecting the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The passage axis of each of the plurality of crossover passages is arranged at a radial angle relative to a localized region of the reference plane such that the radial angle of at least some of the plurality of crossover passages differs in the spanwise direction.

Abstract: A gas turbine engine component has an airfoil extending from a platform to a tip at an end of the airfoil spaced from the platform. The airfoil has a suction wall and a pressure wall, with at least one channel extending toward the tip from the platform. A plenum communicates with the at least one channel. The plenum flows from the suction wall toward the pressure wall at the tip to communicate with cooling holes near the pressure wall. The plenum has a reduced cross-sectional area between the suction wall and the pressure wall, and an increase in cross-sectional area downstream of the reduced cross-sectional area. A mold core is also disclosed.

Abstract: A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge.

Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.

Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.

Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a pocket that faces the interior flow path and extends substantially in a longitudinal direction. The film cooling hole has a portion downstream from the pocket and is arranged at an angle relative to the longitudinal direction and extends to the exterior surface.

Abstract: The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.