Pull-plane effusion combustor panel

1. A heat shield panel for a gas turbine engine combustor extending circumferentially about a longitudinal central axis, comprising:

a hot side defining a first surface having an outer perimeter, the first surface defining a curved base extending circumferentially between a first circumferential end and a second circumferential end of the outer perimeter and axially between an upstream axial end and a downstream axial end of the outer perimeter;

a cold side defining a second surface spaced from the first surface; and

a plurality of holes extending through the heat shield panel circumferentially about the longitudinal central axis, each hole of the plurality of holes including a central axis having vector components that are identical to a common vector, the common vector defined by a common orientation of a plurality of drilling elements spaced along a comb element and configured to drill the plurality of holes simultaneously,

wherein a first group of the plurality of holes is positioned on a first circumferential line extending from the first circumferential end of the outer perimeter of the heat shield panel to the second circumferential end of the outer perimeter of the heat shield panel.

2. The heat shield panel of claim 1 , wherein a second group of the plurality of holes is positioned on a second circumferential line, extending from the first circumferential end to the second circumferential end and offset an axial spacing from the first circumferential line.

3. The heat shield panel of claim 1 , wherein one or more holes within the plurality of holes includes a tapered profile such that a first hole opening positioned on the hot side has a larger cross sectional area than a second hole opening positioned on the cold side.

4. A method of fabricating a heat shield panel for use in a gas turbine engine combustor extending circumferentially about a longitudinal axis, comprising:

forming a panel having a cold side and a hot side, the hot side defining a first surface having an outer perimeter, the first surface defining a curved base extending circumferentially between a first circumferential end and a second circumferential end of the outer perimeter and axially between an upstream axial end and a downstream axial end of the outer perimeter, the cold side defining a second surface spaced from the first surface; and

forming a plurality of holes in the panel, the plurality of holes extending through the heat shield panel circumferentially about the longitudinal central axis, each hole of the plurality of holes including a central axis having vector components that are identical to a common vector, the common vector defined by a common orientation of a plurality of drilling elements spaced along a comb element and configured to drill the plurality of holes simultaneously,

wherein a first group of the plurality of holes is positioned on a first circumferential line extending from the first circumferential end of the outer perimeter of the heat shield panel to the second circumferential end of the outer perimeter of the heat shield panel.

5. The method of claim 4 , wherein forming the panel comprises a casting process.

6. The method of claim 5 , wherein forming the plurality of holes occurs during the casting process.

7. The method of claim 5 , wherein the casting process defines a pull plane having substantially the vector components defining the common vector.

8. The method of claim 4 , wherein forming the plurality of holes comprises one or more of electrical discharge machining, laser drilling and water jet drilling, following casting.

9. The method of claim 8 , wherein the plurality of holes is formed using the comb element configured to form multiple holes simultaneously.

10. The method of claim 9 , wherein the plurality of holes is formed using a plurality of comb elements, each comb element configured to form multiple holes simultaneously.

11. The method of claim 9 , wherein the comb element is configured to traverse the panel in a circumferential direction with respect to the panel and wherein a first subset of the plurality of holes is drilled while the comb element is positioned at a first circumferential location and a second subset of the plurality of holes is drilled while the comb element is positioned at a second circumferential location.

12. A heat shield panel for a gas turbine engine combustor extending circumferentially about a longitudinal central axis, comprising:

a first wall having a hot side defining a first surface having an outer perimeter and a cold side defining a second surface spaced in a radial direction with respect to the longitudinal central axis from the first surface, the first surface defining a curved base extending circumferentially between a first circumferential end and a second circumferential end of the outer perimeter and axially between an upstream axial end and a downstream axial end of the outer perimeter;

a second wall spaced from the first wall in the radial direction such that a cavity is formed between the first wall and the second wall; and

a plurality of holes extending through the first wall circumferentially about the longitudinal central axis, each hole of the plurality of holes including a central axis having vector components that are identical to a common vector, the common vector defined by a common orientation of a plurality of drilling elements spaced along a comb element and configured to drill the plurality of holes simultaneously,

wherein a first group of the plurality of holes is positioned on a first circumferential line extending from the first circumferential end of the outer perimeter of the first wall to the second circumferential end of the outer perimeter of the first wall.

13. The heat shield panel of claim 12 , wherein a second group of the plurality of holes is positioned on a second circumferential line extending from the first circumferential end of the outer perimeter of the first wall to the second circumferential end of the outer perimeter of the first wall.