Dilution/effusion hole pattern for thick combustor panels

1. A combustor panel, comprising:

a dilution hole;

a plurality of film cooling holes, wherein each of the film cooling holes in the plurality of film cooling holes comprise an inlet and an outlet, wherein the outlet is defined by a major axis and a minor axis, wherein the major axis is longer than the minor axis;

a first group of the plurality of film cooling holes arranged circumferentially about the dilution hole, the first group of the plurality extending to encircle an upstream side and a downstream side of the dilution hole, wherein the major axis of each of the outlets of the film cooling holes of the first group are oriented radially toward a center of the dilution hole; and

a second group of the plurality of film cooling holes arranged radially, with respect to the center of the dilution hole, outward of the first group and relatively circumferentially between the first group,

wherein each of the first group of the plurality of film cooling holes and the second group of the plurality of film cooling holes comprise more than one film cooling hole,

wherein each of the outlets of the film cooling holes of the first group have a first outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the first outlet angle is not more than 25° away from the radius extending from the centerline of the dilution hole,

wherein each of the outlets of the second group of the plurality of film cooling holes are arranged in an arcuate segment extending about the center of the dilution hole and downstream thereof,

wherein each of the outlets of the film cooling holes of the second group having a second outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a tangent, at the point of intersection of the major axis and the minor axis of the outlet, to the radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the second outlet angle is not more than 25° away from the tangent.

2. The combustor panel of claim 1 , wherein the first group further comprises first set holes upstream of the dilution hole and second set holes downstream of the dilution hole characterized in that the first set holes have a greater surface concentration than the second set holes,

wherein each of the first set holes and the second set holes comprise more than one film cooling hole.

3. The combustor panel of claim 1 , wherein the first group further comprises first set holes on the upstream side of the dilution hole and second set holes on the downstream side of the dilution hole, wherein the second group of the plurality of film cooling holes are arranged relatively between the second set holes, each of the plurality of film cooling holes of the second group having a second outlet angle oriented in a circumferential direction relatively toward a tangent to a proximate point on a circumference of the dilution hole,

wherein each of the first set holes and the second set holes comprise more than one film cooling hole.

4. The combustor panel of claim 3 , wherein 80% of the outlets of the film cooling holes of the second group have the second outlet angle not more than 25° away from the tangent of the proximate point.

5. The combustor panel of claim 4 , wherein the second group of the plurality of film cooling holes comprises third set holes and fourth set holes, wherein the third set holes are located radially outward of the first set holes and circumferentially between the second set holes and the fourth set holes, wherein the second set holes have a first surface angle between 20° and 75°, wherein the third set holes have a second surface angle between 20° and 65°, and wherein the fourth set holes have a third surface angle between 20° and 70°,

wherein each of the third set holes and the fourth set holes comprise more than one film cooling hole.

6. The combustor panel of claim 3 , further comprising a third group of the plurality of film cooling holes arranged downstream of the second group comprising fifth set holes arranged radially outward of the second group and oriented in a circumferential direction relatively toward the respective tangent of the respective proximate point on the circumference of the dilution hole, wherein the third group further comprises a plurality of downstream set holes each radially outward of the respectively upstream set holes, wherein each of the downstream set holes are characterized by a gradual turning of the respective outlet angle from the respective tangent toward a downstream direction,

wherein each of the third group of the plurality of film cooling holes and the fifth set holes comprise more than one film cooling hole.

7. A combustor assembly comprising:

an inner annular wall;

an outer annular wall about the inner annular wall;

a dome joining the inner annular wall and the outer annular wall,

wherein each of the inner annular wall and the outer annular wall comprise a hot surface defining a combustion chamber therebetween; and

a dilution hole through the hot surface in fluid communication with a respective cold surface;

a plurality of film cooling holes, wherein each of the film cooling holes in the plurality of film cooling holes comprise an inlet on the respective cold surface in fluid communication with an outlet on the respective hot surface, wherein the outlet is defined by a major axis and a minor axis, wherein the major axis is longer than the minor axis;

a first group of the plurality of film cooling holes arranged circumferentially about the dilution hole, the first group of the plurality extending to encircle an upstream side and a downstream side of the dilution hole, wherein the major axis of each of the outlets of the film cooling holes of the first group are oriented radially toward a center of the dilution hole; and

a second group of the plurality of film cooling holes arranged radially, with respect to the center of the dilution hole, outward of the first group and relatively circumferentially between the first group,

wherein each of the first group of the plurality of film cooling holes and the second group of the plurality of film cooling holes comprise more than one film cooling hole,

wherein each of the outlets of the film cooling holes of the first group have a first outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the first outlet angle is not more than 25° away from the radius extending from the centerline of the dilution hole,

wherein each of the outlets of the second group of the plurality of film cooling holes are arranged in an arcuate segment extending about the center of the dilution hole and downstream thereof,

wherein each of the outlets of the film cooling holes of the second group having a second outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a tangent, at the point of intersection of the major axis and the minor axis of the outlet, to the radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the second outlet angle is not more than 25° away from the tangent.

8. The combustor assembly of claim 7 , wherein the first group further comprises first set holes upstream of the dilution hole and second set holes downstream of the dilution hole characterized in that the first set holes have a greater surface concentration than the second set holes,

wherein each of the first set holes and the second set holes comprise more than one film cooling hole.

9. The combustor assembly of claim 7 , wherein the first group further comprises first set holes upstream of the dilution hole and second set holes downstream of the dilution hole wherein the second group of the plurality of film cooling holes are arranged relatively between the second set holes, each of the plurality of film cooling holes of the second group having a second outlet angle oriented in a circumferential direction relatively toward a tangent to a proximate point on a circumference of the dilution hole,

wherein each of the first set holes and the second set holes comprise more than one film cooling hole.

10. The combustor assembly of claim 9 , wherein 80% of the outlets of the film cooling holes of the second group have the second outlet angle not more than 25° away from the tangent of the proximate point.

11. The combustor assembly of claim 10 , wherein the second group of the plurality of film cooling holes comprises third set holes and fourth set holes, wherein the third set holes are located radially outward of the first set holes and circumferentially between the second set holes and the fourth set holes, wherein the second set holes have a first surface angle between 20° and 75°, wherein the third set holes have a second surface angle between 25° and 65°, and wherein the fourth set holes have a third surface angle between 20° and 70°,

wherein each of the third set holes and the fourth set holes comprise more than one film cooling hole.

12. The combustor assembly of claim 9 , further comprising a third group of the plurality of film cooling holes arranged downstream of the second group comprising fifth set holes arranged radially outward of the second group and oriented in a circumferential direction relatively toward the respective tangent of the respective proximate point on the circumference of the dilution hole, wherein the third group further comprises a plurality of downstream set holes each radially outward of the respectively upstream set holes, wherein each of the downstream set holes are characterized by a gradual turning of the respective outlet angle from the respective tangent toward a downstream direction,

wherein each of the third group of the plurality of film cooling holes and the fifth set holes comprise more than one film cooling hole.

13. A gas turbine engine comprising:

a compressor section configured to compress a gas;

a combustor section aft of the compressor section and configured to combust the gas, wherein the combustor section comprises a combustor panel comprising:

a dilution hole;

a plurality of film cooling holes, wherein each of the film cooling holes in the plurality of film cooling holes comprise an inlet and an outlet, wherein the outlet is defined by a major axis and a minor axis, wherein the major axis is longer than the minor axis;

a first group of the plurality of film cooling holes arranged circumferentially about the dilution hole, the first group of the plurality extending to encircle an upstream side and a downstream side of the dilution hole, wherein the major axis of each of the outlets of the film cooling holes of the first group are oriented radially toward a center of the dilution hole; and

a second group of the plurality of film cooling holes arranged radially, with respect to the center of the dilution hole, outward of the first group and relatively circumferentially between the first group,

wherein each of the first group of the plurality of film cooling holes and the second group of the plurality of film cooling holes comprise more than one film cooling hole

wherein each of the outlets of the film cooling holes of the first group have a first outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the first outlet angle is not more than 25° away from the radius extending from the centerline of the dilution hole,

wherein each of the outlets of the second group of the plurality of film cooling holes are arranged in an arcuate segment extending about the center of the dilution hole and downstream thereof,

wherein each of the outlets of the film cooling holes of the second group having a second outlet angle, defined in a plane perpendicular to the centerline of the dilution hole, between the major axis of the outlet and a tangent, at the point of intersection of the major axis and the minor axis of the outlet, to the radius extending from the centerline of the dilution hole to the point of intersection of the major axis and the minor axis of the outlet, wherein the second outlet angle is not more than 25° away from the tangent.

14. The gas turbine engine of claim 13 , wherein the first group further comprises first set holes upstream of the dilution hole and second set holes downstream of the dilution hole characterized in that the first set holes have a greater surface concentration than the second set holes,

wherein each of the first set holes and the second set holes comprise more than one film cooling hole.

15. The gas turbine engine of claim 13 , wherein the first group further comprises first set holes upstream of the dilution hole and second set holes downstream of the dilution hole, wherein the second group of the plurality of film cooling holes are arranged relatively between the second set holes,

wherein each of the first set holes and the second set holes comprise more than one film cooling hole.

16. The gas turbine engine of claim 15 , wherein the second group of the plurality of film cooling holes comprises third set holes and fourth set holes, wherein the third set holes are located radially outward of the first set holes and circumferentially between the second set holes and the fourth set holes, wherein the second set holes have a first surface angle between 20° and 75°, wherein the third set holes have a second surface angle between 25° and 65°, and wherein the fourth set holes have a third surface angle between 20° and 70°,

wherein each of the third set holes and the fourth set holes comprise more than one film cooling hole.

17. The gas turbine engine of claim 15 , further comprising a third group of the plurality of film cooling holes arranged downstream of the second group comprising fifth set holes arranged radially outward of the second group and oriented in a circumferential direction relatively toward the respective tangent of the respective proximate point on the circumference of the dilution hole, wherein the third group further comprises a plurality of downstream set holes each radially outward of the respectively upstream set holes, wherein each of the downstream set holes are characterized by a gradual turning of the respective outlet angle from the respective tangent toward a downstream direction,

wherein each of the third group of the plurality of film cooling holes and the fifth set holes comprise more than one film cooling hole.