Core arrangement for turbine engine component
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.
1. A casting core for an airfoil, comprising:
a first portion extending in a first direction and corresponding to a first cavity of an airfoil, the first portion defining 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; and
wherein the plurality of grooves includes a first set of grooves that extend a length along the respective groove axis such that the first set of grooves are substantially straight, the respective groove axis of each of the first set of grooves is parallel to the pull direction, and the groove axis of each of the plurality of grooves extends longitudinally between a first end and an opposed, second end of the respective groove of the plurality of grooves.
2. The casting core for an airfoil as recited in claim 1 , wherein the groove axis of each of the plurality of grooves is arranged at a radial angle relative to the reference plane such that the radial angle of each of the first set of grooves is the same in the first direction.
3. The casting core for an airfoil as recited in claim 1 , wherein the plurality of grooves includes the first set of grooves oriented with respect to the pull direction and a second set of grooves, the second set of grooves corresponding to a second set of trip strips of the airfoil, and the second set of grooves are distributed in the first direction such that each groove axis of the respective second set of grooves is transverse to the pull direction of the casting die.
4. The casting core for an airfoil as recited in claim 3 , wherein at least some grooves of the second set of grooves extend from at least some grooves of the first set of grooves.
5. The casting core for an airfoil as recited in claim 4 , wherein the groove axis of each of the second set of grooves is arranged at a radial angle relative to the reference plane such that the groove axis has a component that extends in the first direction, the first direction corresponding to a radial direction of the airfoil, and the airfoil including an airfoil body extending in the radial direction from a platform and extending in a thickness direction between a pressure side and a suction side, with the reference plane extending in the radial direction and extending in an axial direction between a leading edge and a trailing edge of the airfoil body.
6. The casting core for an airfoil as recited in claim 1 , comprising:
a second portion extending in the first direction and corresponding to a feeding cavity of the airfoil, the second portion defined by the casting die; and
wherein the first cavity is an impingement cavity located at a leading edge of the airfoil and in communication with the feeding cavity.
7. The casting core for an airfoil as recited in claim 1 , wherein the parting line is curvilinear.
8. The casting core for an airfoil as recited in claim 1 , wherein the plurality of grooves are spaced apart from the parting line.
9. The casting core for an airfoil as recited in claim 8 , comprising:
a second portion extending in the first direction and corresponding to a feeding cavity of the airfoil, the second portion defined by the casting die; and
wherein the first cavity is an impingement cavity located at a trailing edge of the airfoil and in communication with the feeding cavity.
10. The casting core for an airfoil as recited in claim 8 , wherein the first side corresponds to one of a pressure side and a suction side of the airfoil, and the reference plane defines a second side opposite the first side that corresponds to another one of the pressure side and the suction side, with the reference plane extending in a radial direction with respect to the airfoil to separate the pressure side and the suction side.
11. The casting core for an airfoil as recited in claim 10 , wherein the casting die is a first casting die, and further comprising a second casting die, the first portion arranged between the first casting die and the second casting die that abuts against the first casting die to form the parting line.