Effusion cooling for dilution/quench hole edges in combustor liner panels

1. A gas turbine engine component, comprising:

a first surface and a second surface;

a dilution hole defined by the first surface and the second surface;

a plurality of first effusion holes located circumferentially about, at least, a portion of the dilution hole, wherein each first effusion hole of the plurality of first effusion holes has a first inlet defined by the second surface and a first outlet defined by the first surface; and

a plurality of second effusion holes interleaved circumferentially with the plurality of first effusion holes about the portion of the dilution hole, wherein each second effusion hole of the plurality of second effusion holes has a second inlet defined by the second surface and a second outlet defined by the first surface, and wherein the first outlet of each first effusion hole of the plurality of first effusion holes is located nearer to the dilution hole than the second outlet of each second effusion hole of the plurality of second effusion holes,

wherein the first inlet of each first effusion hole of the plurality of first effusion holes is located at a same distance from the dilution hole as the second inlet of each second effusion hole of the plurality of second effusion holes, and

wherein the first outlet of each first effusion hole of the plurality of first effusion holes and the second outlet of each second effusion hole of the plurality of second effusion holes are located on a same plane defined by the first surface.

2. The gas turbine engine component of claim 1 , further comprising a grommet defined by the second surface, wherein the first inlet of each first effusion hole of the plurality of first effusion holes and the second inlet of each second effusion hole of the plurality of second effusion holes are defined by the grommet.

3. The gas turbine engine component of claim 1 , further comprising a tangential effusion hole having a longitudinal axis extending at a tangential angle relative to a linear longitudinal axis of at least one of a first effusion hole of the plurality of first effusion holes or a second effusion hole of the plurality of second effusion holes, the tangential angle being between 60 degrees and 120 degrees, wherein the tangential effusion hole has a tangential inlet defined by the second surface and a tangential outlet defined by the first surface.

4. The gas turbine engine component of claim 3 , wherein the tangential outlet is aligned with the first inlet of the first effusion hole of the plurality of first effusion holes.

5. The gas turbine engine component of claim 1 , wherein the gas turbine engine component is a panel that at least partially defines a combustion chamber of a gas turbine engine such that the first surface is exposed to combustion in the combustion chamber.

6. The gas turbine engine component of claim 1 , wherein the first outlet of each first effusion hole of the plurality of first effusion holes and the second outlet of each second effusion hole of the plurality of second effusion holes are closer to the dilution hole than the first inlet of each first effusion hole of the plurality of first effusion holes and the second inlet of each second effusion hole of the plurality of second effusion holes, respectively.

7. The gas turbine engine component of claim 5 , wherein each first effusion hole of the plurality of first effusion holes forms a first angle with respect to the first surface, and wherein each second effusion hole of the plurality of second effusion holes forms a second angle with respect to the first surface, and wherein the first angle is equal to the second angle.

8. A gas turbine engine component, comprising:

a first surface and a second surface;

a dilution hole defined by the first surface and the second surface;

a plurality of first effusion holes located circumferentially about, at least, a portion of the dilution hole, wherein each first effusion hole of the plurality of first effusion holes has a first inlet defined by the second surface and a first outlet defined by the first surface, wherein each first effusion hole of the plurality of first effusion holes is oriented at a first angle of between 20 degrees and 45 degrees relative to the first surface; and

a plurality of second effusion holes interleaved circumferentially with the plurality of first effusion holes about the portion of the dilution hole, wherein each second effusion hole of the plurality of second effusion holes has a second inlet defined by the second surface and a second outlet defined by the first surface, wherein each second effusion hole of the plurality of second effusion holes is oriented at a second angle of between 20 degrees and 55 degrees relative to the first surface, and wherein the first outlet of each of the first effusion hole of the plurality of first effusion holes is located nearer to the dilution hole than the second outlet of each of the second effusion hole of the plurality of second effusion holes,

wherein the first inlet of each first effusion hole of the plurality of first effusion holes is located at a same distance from the dilution hole as the second inlet of each second effusion hole of the plurality of second effusion holes, and

wherein the first outlet of the first effusion hole and the second outlet of the second effusion hole are both located on a same plane defined by the first surface.

9. The gas turbine engine component of claim 8 , further comprising a grommet defined by the second surface, wherein the first inlet of each first effusion hole and the second inlet of each second effusion hole are defined by the grommet.

10. The gas turbine engine component of claim 8 , further comprising a tangential effusion hole having a longitudinal axis extending at a tangential angle relative to a linear longitudinal axis of at least one of a first effusion hole of the plurality of first effusion holes or a second effusion hole of the plurality of second effusion holes, wherein the tangential angle is between 60 degrees and 120 degrees, and wherein the tangential effusion hole has a tangential inlet defined by the second surface and a tangential outlet defined by the first surface.

11. The gas turbine engine component of claim 10 , wherein the tangential outlet is aligned with the first inlet of the first effusion hole of the plurality of first effusion holes.

12. The gas turbine engine component of claim 8 , wherein the gas turbine engine component is a panel that at least partially defines a combustion chamber of a gas turbine engine such that the first surface is exposed to combustion in the combustion chamber.

13. The gas turbine engine component of claim 8 , wherein the first outlet of the first effusion hole and the second outlet of the second effusion hole are closer to the dilution hole than the first inlet of the first effusion hole and the second inlet of the second effusion hole, respectively.

14. A liner and shell assembly, comprising:

a shell; and

a panel at least partially spaced from the shell to form a gap therebetween, the panel having:

a first surface and a second surface;

a dilution hole at least partially defined by the first surface and the second surface, and

a plurality of first effusion holes located circumferentially about, at least, a portion of the dilution hole, wherein each first effusion hole of the plurality of first effusion holes has having a first inlet and a first outlet, the first inlet being located at the gap between the panel and the shell and being defined by the second surface, the first outlet being defined by the first surface; and

a plurality of second effusion holes interleaved circumferentially with the plurality of first effusion holes about the portion of the dilution hole, wherein each second effusion hole of the plurality of second effusion holes has a second inlet and a second outlet, the second inlet being located at the gap between the panel and the shell and being defined by the second surface, the second outlet being defined by the first surface, wherein the first outlet of each first effusion hole of the plurality of first effusion holes is located nearer to the dilution hole than the second outlet of each second effusion hole of the plurality of second effusion holes,

wherein the first inlet of each first effusion hole of the plurality of first effusion holes is located at a same distance from the dilution hole as the second inlet of each second effusion hole of the plurality of second effusion holes, and

wherein the first outlet of the first effusion hole and the second outlet of the second effusion hole are located on a same plane defined by the first surface.

15. The liner and shell assembly of claim 14 , wherein the panel further includes a grommet defined by the second surface of the panel, and wherein the first inlet of each first effusion hole of the plurality of first effusion holes and the second inlet of each second effusion hole of the plurality of second effusion holes are defined by the grommet.

16. The liner and shell assembly of claim 14 , wherein the panel further includes a tangential effusion hole extending at an angle of between 60 degrees and 120 degrees relative to at least one of a first effusion hole of the plurality of first effusion holes or a second effusion hole of the plurality of second effusion holes, the tangential effusion hole having a tangential inlet defined by the second surface and a tangential outlet defined by the first surface.