Turbine blade trailing edge construction
A turbine blade system for a gas turbine engine includes a turbine blade having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface to a trailing edge. The trailing edge region includes a plurality of riblets extending in the lengthwise direction from the pressure side surface toward the trailing edge. The trailing edge region defines a plurality of ejection slots each laterally disposed between two of the riblets. The plurality of riblets each define an upper surface having at least a portion in the lengthwise direction being curved relative to the pressure side surface so as to generally shield the upper surface from a high heat load propagating from the pressure side surface and to facilitate cooling air flowing from the ejection slots to flow over the upper surface.
1. A turbine blade system for a gas turbine engine, the turbine blade system comprising a turbine blade having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface to a trailing edge, the trailing edge region including a plurality of riblets extending in the lengthwise direction from the pressure side surface toward the trailing edge, the trailing edge region defining a plurality of ejection slots, each laterally disposed between two of the riblets, the riblets each having an upper surface comprising an extension of said pressure side surface, said extension being external of said turbine blade, each said upper riblet surface having a substantial portion thereof in the lengthwise direction which is of increased curvature relative to the pressure side surface wherein the upper surface of each said riblet is shielded from a high heat load propagating from the pressure side surface and wherein the flow of cooling air flowing from the ejection slots over the upper surface of each said riblet is facilitated.
2. A turbine blade system as defined in claim 1 , wherein the upper surface associated with each of the plurality of riblets includes differential segments which are generally flat or linear in the lateral direction.
3. A turbine blade system as defined in claim 2 , wherein the plurality of riblets each extend in the lengthwise direction from a first end adjacent to the pressure side surface to a second end located inwardly of the trailing edge.
4. A turbine blade system as defined in claim 1 , wherein each of the upper surfaces associated with the plurality of riblets has at least a portion thereof in the lateral direction which is curved so as to further facilitate cooling air flowing from the ejection slots over the upper surfaces.
5. A turbine blade system as defined in claim 1 , wherein each said portion of said upper surface of increased curvature associated with each of the plurality of riblets is inwardly curved relative to the pressure side surface.
6. A turbine blade system as defined in claim 1 , wherein the upper surface associated with each of the plurality of riblets has at least a portion in the lengthwise direction being generally concavely curved relative to the pressure side surface.
7. A turbine blade system as defined in claim 1 , wherein each of the upper surfaces associated with the plurality of riblets has at least a portion in the lateral direction which is generally convexly curved so as to further facilitate cooling air flowing from the ejection slots over the upper surfaces.
8. A turbine blade system as defined in claim 7 , wherein the plurality or riblets each have a width progressively decreasing in the lengthwise direction from the pressure side surface toward the trailing edge.
9. A turbine blade system as defined in claim 7 , wherein the plurality of riblets each have a width progressively decreasing in the lengthwise direction from the pressure side surface toward the trailing edge such that the width converges to a point at a location slightly inwardly of the trailing edge.
10. A turbine blade system for a gas turbine engine, the turbine blade system comprising a turbine blade having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface to a trailing edge, the trailing edge region including a plurality of riblets extending in the lengthwise direction from the pressure side surface toward the trailing edge, the trailing edge region defining a plurality of ejection slots each laterally disposed between two of the riblets, the plurality of riblets each defining an upper surface comprising an extension of said pressure side surface, said upper riblet surfaces each having at least a substantial portion thereof in the lengthwise direction which is inwardly concavely curved relative to the pressure side surface wherein the upper surfaces of said riblets are shielded from a high heat load propagating from the pressure side surface and wherein the flow of cooling air flowing from the ejection slots over the upper surfaces is facilitated, and wherein the upper surface associated with each of the plurality of riblets has at least a substantial portion thereof in the lateral direction being generally convexly curved so as to further facilitate cooling air flowing from the ejection slots over the upper surfaces.