Vane core assemblies and methods
A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.
1. A gas turbine engine comprising:
a compressor section rotatable about an axis;
a combustor in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor, the turbine section including
a vane assembly including a radially outer platform with respect to the axis, a radially inner platform, a first airfoil extending from the radially outer platform to the radially inner platform, a leading edge rail and a trailing edge rail extending radially inward from the inner platform, and a connected passage including an airfoil passage within the first airfoil, a platform passage within the inner platform, and a rail passage within the leading edge rail, wherein the airfoil passage, the platform passage, and the rail passage are fluidly connected.
2. The gas turbine engine as recited in claim 1 , comprising a second airfoil extending from the radially outer platform to the radially inner platform, a second connected passage including a second airfoil passage within the second airfoil, a second platform passage within the inner platform, and a second rail passage within the leading edge rail, wherein the second airfoil passage, the second platform passage, and the second rail passage are fluidly connected.
3. The gas turbine engine as recited in claim 1 , wherein a plurality of cooling holes extend from the platform passage to a gaspath surface of the inner platform.
4. The gas turbine engine as recited in claim 3 , wherein the plurality of cooling holes extend toward a trailing edge of the platform as they extend toward the gaspath surface.
5. The gas turbine engine as recited in claim 1 , wherein the airfoil passage forms a leading edge cavity and a second cavity spaced toward a trailing edge of the airfoil from the leading edge cavity, and both the leading edge cavity and the second cavity are fluidly connected with the platform passage.
6. The gas turbine engine as recited in claim 1 , comprising a cooling air source configured to supply cooling air from the outer platform through the airfoil passage, and from the airfoil passage to the platform passage.
7. The gas turbine engine as recited in claim 6 , wherein a plurality of cooling holes extend from the platform passage to a gaspath surface of the inner platform, and are configured to allow at least a portion of the cooling air in the platform passage to exit through the plurality of cooling holes.
8. The gas turbine engine as recited in claim 1 , wherein the turbine comprises:
a first row of vanes;
a second row of vanes aft of the first row of vanes;
a row of blades axially between the first row of vanes and second row of vanes;
the second row of vanes including the vane assembly.
9. The gas turbine engine as recited in claim 8 , wherein the second row of vanes includes a second vane assembly identical to the vane assembly.
10. A vane assembly for a gas turbine engine, comprising an outer platform; an inner platform; a first airfoil extending from the outer platform to the inner platform; a leading edge rail and a trailing edge rail extending from the inner platform in a direction away from the first airfoil; a connected passage including an airfoil passage within the first airfoil, a platform passage within the inner platform, and a rail passage within the leading edge rail, wherein the airfoil passage, the platform passage, and the rail passage are fluidly connected; and a plurality of cooling holes extending from the platform passage to a gaspath surface of the inner platform.
11. The vane assembly as recited in claim 10 , comprising a second airfoil extending from the outer platform to the inner platform, wherein the platform passage is aligned circumferentially between a pressure side of the first airfoil and a suction side of the second airfoil.
12. The vane assembly as recited in claim 10 , comprising a second airfoil extending from the outer platform to the inner platform, a second connected passage including a second airfoil passage within the second airfoil, a second platform passage within the inner platform, and a second rail passage within the leading edge rail, wherein the second airfoil passage, the second platform passage, and the second rail passage are fluidly connected.
13. The vane assembly as recited in claim 12 , wherein the platform passage is aligned circumferentially between a pressure side of the first airfoil and a suction side of the second airfoil, and the second platform passage is aligned circumferentially between a pressure side of the second airfoil and a mate face of the platform.
14. The vane assembly as recited in claim 11 , wherein the plurality of cooling holes extend toward a trailing edge of the platform as they extend toward the gas path surface.
15. The gas turbine engine as recited in claim 1 , wherein the leading edge of the platform passage is aft of the leading edge of the airfoil.
16. A vane assembly for a gas turbine engine, comprising
an outer platform;
an inner platform;
a first airfoil extending from the outer platform to the inner platform;
a leading edge rail and a trailing edge rail extending from the inner platform in a direction away from the first airfoil; a connected passage including an airfoil passage within the first airfoil, a platform passage within the inner platform, and a rail passage within the leading edge rail, wherein the airfoil passage, the platform passage, and the rail passage are fluidly connected, wherein the leading edge of the platform passage is aft of the leading edge of the airfoil; and a plurality of cooling holes extending from the platform passage to a gaspath surface of the inner platform extending toward a trailing edge of the platform as they extend toward the gas path surface; a second airfoil extending from the outer platform to the inner platform; a second connected passage including a second airfoil passage within the second airfoil, a second platform passage within the inner platform, and a second rail passage within the leading edge rail, wherein the second airfoil passage, the second platform passage, and the second rail passage are fluidly connected, the leading edge of the second platform passage is aft of the leading edge of the second airfoil, the platform passage is aligned circumferentially between a pressure side of the first airfoil and a suction side of the second airfoil, and the second platform passage is aligned circumferentially between a pressure side of the second airfoil and a mate face of the platform.
17. The vane assembly as recited in claim 16 , comprising a second plurality of cooling holes extending from the second platform passage to a gaspath surface of the inner platform extending toward a trailing edge of the platform as they extend toward the gas path surface.
18. The vane assembly as recited in claim 16 , wherein the airfoil passage forms a leading edge cavity and a second cavity spaced toward a trailing edge of the airfoil from the leading edge cavity, and both the leading edge cavity and the second cavity are fluidly connected with the platform passage; and
the second airfoil passage forms a third cavity and a fourth cavity spaced toward a trailing edge of the airfoil from the third cavity, and both the third cavity and the fourth cavity are fluidly connected with the second platform passage.