Combustor bulkhead with circular impingement hole pattern
A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. The combustor further includes a bulkhead extending between the inner shell and the outer shell. The bulkhead includes a plurality of impingement cooling rings. Each impingement cooling ring of the plurality of impingement cooling rings includes a plurality of impingement cooling holes extending through the bulkhead. The combustor further includes a heat shield panel mounted to the bulkhead so as to define an impingement cooling chamber between the bulkhead and the heat shield panel. The heat shield panel further includes a radial portion between a perimeter and an opening, with respect to an opening center axis, which is free of penetrations. The plurality of impingement cooling holes of each of the plurality of impingement cooling rings are directed toward the radial portion of the heat shield panel.
1. A combustor for a gas turbine engine, the combustor comprising:
a combustion chamber defined between an inner shell and an outer shell;
a bulkhead extending between the inner shell and the outer shell, the bulkhead comprising a plurality of impingement cooling rings, each impingement cooling ring of the plurality of impingement cooling rings comprising a plurality of impingement cooling holes extending through the bulkhead; and
a heat shield panel comprising a first surface facing the combustion chamber and a second surface opposite the first surface and facing the bulkhead, the heat shield panel mounted to the bulkhead so as to define an impingement cooling chamber between the bulkhead and the heat shield panel, the heat shield panel further comprising a perimeter and an opening extending through the heat shield panel between the first surface and the second surface, the opening centered about an opening center axis, the heat shield panel further comprising a radial portion between the perimeter and the opening, with respect to the opening center axis, which is free of penetrations;
wherein the plurality of impingement cooling holes of each of the plurality of impingement cooling rings are directed toward the radial portion of the heat shield panel;
wherein the plurality of impingement cooling rings are concentrically disposed about the opening center axis; and
wherein the plurality of impingement cooling rings are radially spaced such that a first radial distance between adjacent impingement cooling rings of the plurality of impingement cooling rings decreases as a second radial distance from the opening center axis increases.
2. The combustor of claim 1 , wherein a first plurality of impingement cooling holes of a first impingement cooling ring of the plurality of impingement cooling rings is offset with respect to a second plurality of impingement cooling holes of an adjacent second impingement cooling ring of the plurality of impingement cooling rings.
3. The combustor of claim 1 , wherein the heat shield panel comprises a first plurality of effusion holes extending through the heat shield panel and disposed radially between the radial portion and the opening with respect to the opening center axis.
4. The combustor of claim 3 , wherein the heat shield panel further comprises a second plurality of effusion holes extending through the heat shield panel and disposed radially between the radial portion and the perimeter with respect to the opening center axis.
5. The combustor of claim 4 , wherein effusion holes of the first plurality of effusion holes have a greater diameter than effusion holes of the second plurality of effusion holes.
6. The combustor of claim 5 , wherein the radial portion has a first radial length in a direction between an inner diameter position of the opening and an outer diameter position of the perimeter which is greater than 70 percent of a second radial length between the inner diameter position of the opening and the outer diameter position of the perimeter.
7. The combustor of claim 1 , wherein each of the plurality of impingement cooling holes of the plurality of impingement cooling rings are oriented normal to a surface of the bulkhead facing the heat shield panel.
8. The combustor of claim 1 , wherein the radial portion of the heat shield panel comprises a plurality of pin fins extending from the heat shield panel towards the bulkhead.
9. The combustor of claim 8 , wherein the plurality of pin fins has a pin fin height that is between 70 percent and 85 percent of a height of the impingement cooling chamber.
10. The combustor of claim 1 , wherein the plurality of impingement cooling rings comprises at least five impingement cooling rings.
11. A method for cooling a combustor heat shield panel of a gas turbine engine, the method comprising:
providing a bulkhead extending between an inner shell and an outer shell, the inner shell and the outer shell defining a combustion chamber therebetween, the bulkhead comprising a plurality of impingement cooling rings, each impingement cooling ring comprising a plurality of impingement cooling holes extending through the bulkhead;
providing the heat shield panel comprising a first surface facing the combustion chamber and a second surface opposite the first surface and facing the bulkhead, the heat shield panel mounted to the bulkhead so as to define an impingement cooling chamber between the bulkhead and the heat shield panel, the heat shield panel further comprising a perimeter and an opening extending through the heat shield panel between the first surface and the second surface, the opening centered about an opening center axis, the heat shield panel further comprising a radial portion between the perimeter and the opening, with respect to the opening center axis, which is free of penetrations; and
directing an impingement cooling flow toward the radial portion of the heat shield panel with the plurality of impingement cooling holes of each of the plurality of impingement cooling rings;
wherein the plurality of impingement cooling rings are concentrically disposed about the opening center axis; and
wherein the plurality of impingement cooling rings are radially spaced such that a first radial distance between adjacent impingement cooling rings of the plurality of impingement cooling rings decreases as a second radial distance from the opening center axis increases.
12. The method of claim 11 , further comprising:
directing a first effusion cooling flow with a first plurality of effusion holes extending through the heat shield panel and disposed radially between the radial portion and the opening with respect to the opening center axis; and
directing a second effusion cooling flow with a second plurality of effusion holes extending through the heat shield panel and disposed radially between the radial portion and the perimeter with respect to the opening center axis.
13. The method of claim 12 , wherein the radial portion of the heat shield panel comprises a plurality of pin fins extending from the heat shield panel towards the bulkhead.
14. The method of claim 13 , wherein the plurality of pin fins has a pin fin height that is between 70 percent and 85 percent of a height of the impingement cooling chamber.
15. A combustor for a gas turbine engine, the combustor comprising:
a combustion chamber defined between an inner shell and an outer shell;
a bulkhead extending between the inner shell and the outer shell, the bulkhead comprising a plurality of impingement cooling rings, each impingement cooling ring of the plurality of impingement cooling rings comprising a plurality of impingement cooling holes extending through the bulkhead; and
a heat shield panel comprising a first surface facing the combustion chamber and a second surface opposite the first surface and facing the bulkhead, the heat shield panel mounted to the bulkhead so as to define an impingement cooling chamber between the bulkhead and the heat shield panel, the heat shield panel further comprising a perimeter and an opening extending through the heat shield panel between the first surface and the second surface, the opening centered about an opening center axis, the heat shield panel further comprising a radial portion between the perimeter and the opening, with respect to the opening center axis, which is free of penetrations;
wherein the plurality of impingement cooling holes of each of the plurality of impingement cooling rings are directed toward the radial portion of the heat shield panel;
wherein the plurality of impingement cooling rings are concentrically disposed about the opening center axis;
wherein the heat shield panel comprises a first plurality of effusion holes extending through the heat shield panel and disposed radially between the radial portion and the opening with respect to the opening center axis
wherein the heat shield panel further comprises a second plurality of effusion holes extending through the heat shield panel and disposed radially between the radial portion and the perimeter with respect to the opening center axis
wherein effusion holes of the first plurality of effusion holes have a greater diameter than effusion holes of the second plurality of effusion holes.