Airfoil with variable trip strip height
An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.
1. An airfoil component for a gas turbine engine comprising:
an airfoil extending from a platform, the platform including a cooling passage defined by a surface, wherein the airfoil component is a turbine vane having an inner and an outer platform, wherein the turbine vane includes a pair of airfoils extending radially from the same inner platform, wherein the cooling passage is provided in the inner platform of the turbine vane, wherein the cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage, the first radially extending leg provides an inlet to the cooling passage, and the second radially extending leg is plugged; and
chevron-shaped trip strips extending from the surface into the cooling passage at a trip strip height along a length, the trip strip height varying along the length, the circumferential passage including the trip strips, the trip strips arranged on either of opposing sides of the first radially extending leg with the chevron-shape on each of the opposing sides facing opposing directions.
2. The airfoil component according to claim 1 , wherein the length is provided by multiple zones, the height varying between the zones.
3. The airfoil component according to claim 2 , wherein the multiple zones include first, second and third cooling passage heights, and the trip strip includes first, second and third trip strip heights respectively within the first, second and third zones.
4. The airfoil component according to claim 1 , wherein the chevrons are provided by first and second legs joined to one another at an apex to provide the chevron-shaped trip strips.
5. The airfoil component according to claim 3 , wherein a trip strip portion within each of the multiple zone includes a p/e ratio, wherein p corresponds to a pitch that provides a spacing between adjacent trip strips, and e corresponds to the trip strip height, the trip strip portions having p/e ratio in the range of 3-20.
6. The airfoil component according to claim 5 , wherein the p/e ratio range is 3.0-5.5.
7. The airfoil component according to claim 3 , wherein the trip strip includes an e/h ratio, wherein e corresponds to a trip strip height and h corresponds to the cooling passage height, the e/h ratio of the trip strip in a range of 0.05-0.40.
8. The airfoil component according to claim 7 , wherein the e/h ratio range is 0.10-0.30.
9. The airfoil component according to claim 3 , wherein the first and third zones each include a constant trip strip height that are different than one another, and the second zone includes a varying trip strip height.
10. A turbine vane for a gas turbine engine comprising:
inner and outer platforms, and a cooling passage is provided in the inner platform, wherein the cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage, wherein the second leg is plugged to obstruct airflow therethrough;
a pair of airfoils extending radially from the same inner platform; and
a trip strip extending from a surface of the circumferential passage into the circumferential passage at a trip strip height along a length, the trip strip height varying along the length.
11. The turbine vane according to claim 10 , wherein the trip strip is chevron-shaped.
12. The airfoil component according to claim 1 , wherein the trip strip height varies along its length with a height of the cooling passage.
13. The airfoil component according to claim 12 , wherein the trip strip height increases along its length as the height of the cooling passage increases.