Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a rotor and a vane spaced axially from the rotor, and a blade outer air seal spaced radially from the rotor. At least one of the rotor and the vane includes an airfoil section extending from a platform. At least one of the airfoil section, the platform and the blade outer air seal includes a first cavity extending in a first direction, the first cavity defining a reference plane along a parting line formed by a casting die, and a plurality of trip strips including a first set of trip strips distributed in the first direction along a surface of the first cavity and on a first side of the reference plane, each of the plurality of trip strips defining a respective groove axis extending longitudinally between a first end and an opposed, second end of a respective one the plurality of trip strips, and the groove axes being oriented with respect to a pull direction of the casting die.

Abstract: A core assembly for a casting system according to an exemplary aspect of the present disclosure includes, among other things, a core that includes a body and at least one hole formed through the body and a spacer that extends through the at least one hole. The spacer includes a stud portion and a chaplet portion configured to abut a surface of the body that circumscribes the at least one hole.

Abstract: A mold for manufacturing a casted workpiece is, at least in-part, manufactured utilizing an additive manufacturing process. The mold may have a core having non-line-of-sight features that are additively manufactured and in contact with an outer shell of a wax mold and/or an outer shell of a casting mold of the mold. The outer shell of either the wax or casting molds may also be additively manufactured, and the shell of the casting mold may be additively manufactured as one unitary piece to the core.

Abstract: A casting core may comprise a tip flag material having a forward cavity and a first spear cavity disposed aft of the forward cavity. A trailing edge discharge material may be separated from the tip flag material and include a first row of cavities. The first row of cavities may comprise a first racetrack cavity. A second row of cavities may be disposed aft of the first row of cavities and include a second racetrack cavity. A third row of cavities may be disposed aft of the second row of cavities and include a circular cavity. A fourth row of cavities may be disposed aft of the third row of cavities and include a second spear cavity.

Abstract: A component for a gas turbine engine includes an exterior surface that provides pressure and suction sides. A cooling passage in the component includes a serpentine passageway that has first and second passes respectively configured to provide fluid flow in opposite directions from one another. The first pass includes first and second portions nested relative to one another and overlapping in a thickness direction. The first and second portions are adjacent to one another by sharing a common wall. The first portion is provided on the suction side. The second portion is provided on the pressure side.

Abstract: In a featured embodiment, a gas turbine engine component comprises an airfoil having a leading edge, a trailing edge, and pressure and suction side walls extending from the leading edge to the trailing edge. The airfoil extends from a base to a tip. A shelf is formed in the tip, and extends from the pressure side wall, around the leading edge, to the suction side wall.

Abstract: A casting core and/or an airfoil may comprise a tip flag cavity having a forward pedestal and a first spear pedestal disposed aft of the forward pedestal. A trailing edge discharge cavity may be separated from the tip flag cavity and include a first row of pedestals. The first row of pedestals may comprise a first racetrack pedestal. A second row of pedestals may be disposed aft of the first row of pedestals and include a second racetrack pedestal. A third row of pedestals may be disposed aft of the second row of pedestals and include a circular pedestal. A fourth row of pedestals may be disposed aft of the third row of pedestals and include a second spear pedestal.

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.

Abstract: A casting core and/or an airfoil may comprise a tip flag cavity having a forward pedestal and a first spear pedestal disposed aft of the forward pedestal. A trailing edge discharge cavity may be separated from the tip flag cavity and include a first row of pedestals. The first row of pedestals may comprise a first racetrack pedestal. A second row of pedestals may be disposed aft of the first row of pedestals and include a second racetrack pedestal. A third row of pedestals may be disposed aft of the second row of pedestals and include a circular pedestal. A fourth row of pedestals may be disposed aft of the third row of pedestals and include a second spear pedestal.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a rotor and a vane spaced axially from the rotor, and a blade outer air seal spaced radially from the rotor. At least one of the rotor and the vane includes an airfoil section extending from a platform. At least one of the airfoil section, the platform and the blade outer air seal includes a first cavity extending in a first direction, the first cavity defining a reference plane along a parting line formed by a casting die, and a plurality of trip strips including a first set of trip strips distributed in the first direction along a surface of the first cavity and on a first side of the reference plane, each of the plurality of trip strips defining a respective groove axis extending longitudinally between a first end and an opposed, second end of a respective one the plurality of trip strips, and the groove axes being oriented with respect to a pull direction of the casting die.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a body, a wall extending inside of the body and a plurality of vortex promoting features arranged in a helical pattern along the wall.

Abstract: A casting core for an airfoil according to an example of the present disclosure includes, among other things, a first portion extending in a first direction and corresponding to a first cavity of an airfoil. The first portion defines a reference plane along a parting line formed by a casting die. The first portion defines a plurality of grooves corresponding to a plurality of trip strips of the airfoil. Each of the plurality of grooves defines a respective groove axis, and the plurality of grooves are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes are oriented with respect to a pull direction of the casting die. A method for fabricating a gas turbine engine component is also disclosed.

Abstract: A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.

Abstract: A core assembly for a casting system according to an exemplary aspect of the present disclosure includes, among other things, a core that includes a body and at least one hole formed through the body and a spacer that extends through the at least one hole. The spacer includes a stud portion and a chaplet portion configured to abut a surface of the body that circumscribes the at least one hole.

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.

Abstract: A core assembly for a casting system according to an exemplary aspect of the present disclosure includes, among other things, a core that includes a body and at least one hole formed through the body and a spacer that extends through the at least one hole. The spacer includes a stud portion and a chaplet portion configured to abut a surface of the body that circumscribes the at least one hole.

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.

Abstract: A core assembly for a casting system according to an exemplary aspect of the present disclosure includes, among other things, a core that includes a body and at least one hole formed through the body and a spacer that extends through the at least one hole. The spacer includes a stud portion and a chaplet portion configured to abut a surface of the body that circumscribes the at least one hole.

Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.

Abstract: A casting core and/or an airfoil may comprise a tip flag cavity having a forward pedestal and a first spear pedestal disposed aft of the forward pedestal. A trailing edge discharge cavity may be separated from the tip flag cavity and include a first row of pedestals. The first row of pedestals may comprise a first racetrack pedestal. A second row of pedestals may be disposed aft of the first row of pedestals and include a second racetrack pedestal. A third row of pedestals may be disposed aft of the second row of pedestals and include a circular pedestal. A fourth row of pedestals may be disposed aft of the third row of pedestals and include a second spear pedestal.