Combustor panel cooling hole arrangement
A cooling hole arrangement for a combustor panel including a first group of cooling holes, each of the first cooling holes extending from a first inlet to a first outlet. Also included is a second group of cooling holes, each of the second cooling holes extending from a second inlet to a second outlet, each of the first cooling holes and the second cooling holes spaced from an edge of the combustor panel in an axial direction to be arranged substantially parallel to the edge of the combustor panel. At least a portion of the first inlet of each first cooling holes is axially overlapped with a portion of the second inlet of the second cooling holes. The first outlet of each of the first cooling holes is closer to the edge of the combustor panel than the second outlet of the second cooling holes is to the edge.
1. A cooling hole arrangement for a combustor panel comprising:
a plurality of cooling holes that are located closest to an edge of the combustor panel, relative to every other cooling holes of the combustor panel, the plurality of cooling holes comprising:
a first group of cooling holes located in a first row, each of the first group of cooling holes extending from a first inlet to a first outlet; and
a second group of cooling holes located in a second row adjacent to the first row, each of the second group of cooling holes extending from a second inlet to a second outlet, each of the first group of cooling holes and the second group of cooling holes spaced from the edge of the combustor panel in an axial direction to be arranged parallel to the edge of the combustor panel, wherein the first row is located closer to the edge of the combustor panel than the second row,
wherein at least a portion of the first inlet of each first group of cooling holes axially overlapped with a portion of the second inlet of the second group of cooling holes,
the first outlet of each of the first group of cooling holes being closer to the edge of the combustor panel than the second outlet of the second group of cooling holes is to the edge.
2. The cooling hole arrangement of claim 1 , wherein each of the first group of cooling holes extend from the first inlet to the first outlet at a first angular orientation, each of the second group of cooling holes extending from the second inlet to the second outlet at a second angular orientation, the first angular orientation ranging from about 10 degrees to about 50 degrees relative to a circumferential direction.
3. The cooling hole arrangement of claim 1 , wherein each of the first group of cooling holes extend from the first inlet to the first outlet at a first angular orientation, each of the second group of cooling holes extending from the second inlet to the second outlet at a second angular orientation, the second angular orientation ranging from about −15 degrees to about 15 degrees relative to a circumferential direction.
4. The cooling hole arrangement of claim 1 , wherein a distance between the second outlet and the edge is about 3 times to about 4 times greater than the distance between the first outlet and the edge.
5. The cooling hole arrangement of claim 1 , wherein a distance between the second outlet and the edge is about 3.4 times greater than the distance between the first outlet and the edge.
6. The cooling hole arrangement of claim 1 , wherein each of the first group of cooling holes extend from the first inlet to the first outlet at a first angular orientation, the first angular orientation not parallel to an oncoming gas flow path direction.
7. A cooling hole arrangement for a combustor panel comprising: a plurality of cooling holes that are located closest to a leading edge of the combustor panel, relative to every other cooling holes of the combustor panel, the plurality of cooling holes comprising: a first group of cooling holes located in a first row, the first group of cooling holes having a first angular orientation; and a second group of cooling holes located in a second row adjacent to the first row, the second group of cooling holes having a second angular orientation, wherein the first angular orientation different than the second angular orientation, each of the first group of cooling holes and the second group of cooling holes spaced from the leading edge of the combustor panel in an axial direction to be arranged parallel to the leading edge of the combustor panel, wherein the first row is located closer to the edge of the combustor panel than the second row, wherein each of the first group of cooling holes extends from a first inlet to a first outlet, each of the second group of cooling holes extending from a second inlet to a second outlet, at least a portion of the first inlet of each first group of cooling holes axially overlapped with a portion of the second inlet of the second group of cooling holes.
8. The cooling hole arrangement of claim 7 , wherein the first outlet of each of the first group of cooling holes is closer to a leading edge of the combustor panel than the second outlet of the second group of cooling holes is to the leading edge.
9. The cooling hole arrangement of claim 7 , wherein the first angular orientation ranges from about 10 degrees to about 50 degrees relative to a circumferential direction.
10. The cooling hole arrangement of claim 7 , wherein the second angular orientation ranging from about −15 degrees to about 15 degrees relative to a circumferential direction.
11. The cooling hole arrangement of claim 8 , wherein a distance between the second outlet and the leading edge is about 3 times to about 4 times greater than the distance between the first outlet and the leading edge.
12. The cooling hole arrangement of claim 7 , wherein the first angular orientation is not parallel to an oncoming gas flow path direction.
13. A gas turbine engine comprising:
a compressor section;
a combustor section;
a turbine section; and
a cooling hole arrangement for a combustor panel of the combustor section, the combustor panel extending axially from a leading edge to a trailing edge, the cooling hole arrangement comprising:
a plurality of cooling holes that are located closest to the leading edge of the combustor panel, relative to every other cooling holes of the combustor panel, the plurality of cooling holes comprising:
a first group of cooling holes located in a first row, the first group of cooling holes having a first angular orientation; and
a second group of cooling holes located in a second row adjacent to the first row, the second group of cooling holes having a second angular orientation, the first angular orientation different than the second angular orientation, each of the first group of cooling holes and the second group of cooling holes spaced from the leading edge of the combustor panel in an axial direction to be arranged parallel to the leading edge of the combustor panel,
wherein the first row is located closer to the edge of the combustor panel than the second row.
14. The gas turbine engine of claim 13 , wherein each of the first group of cooling holes extends from a first inlet to a first outlet, each of the second group of cooling holes extending from a second inlet to a second outlet, at least a portion of the first inlet of each first group of cooling holes axially overlapped with a portion of the second inlet of the second group of cooling holes, the first outlet of each of the first group of cooling holes being closer to a leading edge of the combustor panel than the second outlet of the second group of cooling holes is to the leading edge.
15. The gas turbine engine of claim 13 , wherein the first angular orientation ranges from about 10 degrees to about 50 degrees relative to the circumferential direction.