Trailing edge cooling for a turbine blade
A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.
1. A component for a turbine engine comprising:
an airfoil having an outer surface extending chord-wise from a leading edge to a trailing edge and span-wise from a root to a tip;
a cooling passage located within the airfoil and extending along the trailing edge;
at least one trailing edge cooling channel extending from the cooling passage to the outer surface at the trailing edge, defining a stream-wise flow through the at least one trailing edge cooling channel; and
at least one film hole having an inlet in the cooling passage, an outlet on the outer surface, and a passage connecting the inlet and the outlet; and
at least one turbulator provided in the cooling passage;
wherein the at least one turbulator and the inlet of the at least one film hole are spaced in the cooling passage in a predetermined relationship defining an axis extending between the at least one turbulator and the inlet of the at least one film hole, with the axis arranged orthogonal to the stream-wise flow.
2. The component of claim 1 wherein the inlet is aligned with the at least one trailing edge cooling channel relative to the span-wise direction.
3. The component of claim 2 wherein the inlet of the at least one film hole is aligned with a centerline of the at least one trailing edge cooling channel relative to the stream-wise flow.
4. The component of claim 1 wherein the inlet is stream-wise non-aligned with the at least one trailing edge cooling channel relative to the stream-wise flow.
5. The component of claim 1 wherein the component is one of a rotating blade or a stationary vane.
6. The component of claim 1 wherein the at least one trailing edge cooling channel comprises multiple trailing edge cooling channels.
7. The component of claim 6 wherein the inlet of the at least one film hole is located between two adjacent trailing edge cooling channels of the multiple trailing edge cooling channels in the span-wise direction.
8. The component of claim 7 wherein the at least one film hole comprises multiple film holes and the inlets of the multiple film holes are located between pairs of adjacent trailing edge cooling channels of the multiple trailing edge cooling channels.
9. A turbine engine comprising:
a core engine comprising a casing at least partially surrounding a high pressure compressor, a combustor, and a high pressure turbine in a serial flow arrangement;
an airfoil, provided in one of the compressor or the combustor, having an outer surface extending chord-wise from a leading edge to a trailing edge and span-wise from a root to a tip;
a cooling passage located within the airfoil and extending along the trailing edge;
at least one trailing edge cooling channel extending from the cooling passage through the trailing edge to define a stream-wise flow through the at least one trailing edge cooling channel;
at least one film hole having an inlet in the cooling passage, an outlet on the outer surface, and a passage connecting the inlet and the outlet; and
at least one turbulator provided in the cooling passage;
wherein the inlet of the at least one film hole is located in the cooling passage in a predetermined relationship to align with the at least one turbulator to define an axis between the at least one turbulator and the inlet of the at least one film hole, with the axis being arranged orthogonal to the stream-wise flow.
10. The turbine engine of claim 9 wherein the inlet of the at least one film hole is aligned with the at least one trailing edge cooling channel relative to the stream-wise flow.
11. The turbine engine of claim 10 wherein the inlet of the at least one film hole is aligned with a centerline of the at least one trailing edge cooling channel relative to the stream-wise flow.
12. The turbine engine of claim 9 wherein the inlet is non-aligned with the at least one trailing edge cooling channel relative to the stream-wise flow.
13. The turbine engine of claim 9 wherein the airfoil is one of a rotating blade or a stationary vane.
14. The turbine engine of claim 9 wherein the at least one trailing edge cooling channel comprises multiple trailing edge cooling channels.
15. The turbine engine of claim 14 wherein the inlet is located between adjacent trailing edge cooling channels of the multiple trailing edge cooling channels.
16. The turbine engine of claim 15 wherein the at least one film hole comprises multiple film holes and the inlets are located between adjacent trailing edge cooling channels.
17. The turbine engine of claim 14 wherein the at least one film hole comprises multiple film holes and the inlets are located in stream-wise alignment with the trailing edge cooling channels.
18. The turbine engine of claim 9 wherein the airfoil is a blade.