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 gas turbine engine comprising:
an airfoil having an outer wall defining a pressure sidewall and a suction sidewall, and 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 one of the trailing edge or the outer wall at the trailing edge;
at least one turbulator located within the at least one trailing edge cooling channel; and
at least one film hole having an inlet in the at least one trailing edge cooling channel, an outlet on the outer wall, and a passage connecting the inlet and the outlet;
wherein the inlet is located in the at least one trailing edge cooling channel in a predetermined relationship to the at least one turbulator; and
wherein the predetermined relationship includes the at least one turbulator being located on one of the pressure sidewall and the suction sidewall, and the inlet of the at least one film hole located on the other of the pressure sidewall and the suction sidewall, with the at least one turbulator and the inlet of the at least one film hole being located in the same stream-wise location.
2. The component of claim 1 wherein the component is one of a rotating blade or a stationary vane.
3. The component of claim 1 wherein the at least one trailing edge cooling channel comprises multiple trailing edge cooling channels.
4. The component of claim 3 wherein the at least one turbulator comprises multiple turbulators within the multiple trailing edge cooling channels.
5. The component of claim 4 wherein the at least one film hole comprises multiple film holes.
6. The component of claim 5 wherein the multiple film holes and multiple turbulators are arranged in pairs within the at least one trailing edge cooling channels, with each film hole having a complementary turbulator.
7. The component of claim 1 wherein the turbulators are stream-wise spaced within the at least one trailing edge cooling channels.
8. The component of claim 1 wherein the at least one turbulator comprises multiple turbulators.
9. The component of claim 8 wherein the at least one film hole comprises multiple film holes, each film hole of the multiple film holes associated with a corresponding one of the multiple turbulators.
10. A component for a gas 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 through one of the trailing edge or the outer surface at the trailing edge;
at least one flow element located within the at least one trailing edge cooling channel; and
at least one film hole having an inlet in the at least one trailing edge cooling channel, an outlet on the outer surface, and a passage connecting the inlet and the outlet;
wherein the inlet is located in the at least one cooling channel in a predetermined relationship to the flow element; and
wherein the predetermined relationship comprises the inlet and the at least one flow element being located on opposite sides of the at least one cooling channel and in the same stream-wise location.
11. The component of claim 10 wherein at least one additional flow element is disposed between the inlets on the at least one cooling channel.
12. The component of claim 11 wherein the predetermined relationship further comprises the inlet and flow element being substantially lined up.
13. The component of claim 10 wherein the at least one trailing edge cooling channel comprises multiple trailing edge cooling channels.
14. The component of claim 13 wherein the at least one flow element comprises multiple flow elements within the multiple trailing edge cooling channels.
15. The component of claim 14 wherein the at least one film hole comprises multiple film holes.
16. The component of claim 15 wherein the multiple film holes and multiple flow elements are arranged in pairs within the multiple trailing edge cooling channels.