Regulated combustor liner panel for a gas turbine engine combustor
A liner panel for use in a combustor of a gas turbine engine, the liner panel including a liner panel with a perimeter rail and a multiple of intermediate rails. A combustor for a gas turbine engine including a support shell and a multiple of liner panels mounted to the support shell via a multiple of studs, each of the multiple of liner panels having a multiple of intermediate rails to form a multiple of circumferential cavities.
1. A liner panel for use Ma combustor of a gas turbine engine, the liner panel comprising:
a perimeter rail that extends from a cold side of the liner panel, the perimeter rail formed by a forward circumferential rail, an aft circumferential rail, and axial rails that interconnect the forward and aft circumferential rails;
a multiple of intermediate rails within the perimeter rail, the multiple of intermediate rails extend from the cold side of the liner panel parallel to the forward circumferential rail and the aft circumferential rail, at least one of the multiple of intermediate rails includes a through aperture;
a dilution passage between two of the multiple of intermediate rails;
a first stud that extends from the cold side of the liner panel between a first one of the multiple of intermediate rails and the forward circumferential rail; and
a second stud that extends from the cold side of the liner panel between a second one of the multiple of intermediate rails and the aft circumferential rail;
wherein a plurality of the multiple of intermediate rails is positioned between the dilution passage and the second stud.
2. The liner panel as recited in claim 1 , wherein the through aperture is parallel to the cold side of the liner panel.
3. The liner panel as recited in claim 2 , wherein the through aperture is parallel to the forward circumferential rail and the aft circumferential rail.
4. The liner panel as recited in claim 1 , wherein the multiple of intermediate rails segment a cavity between the liner panel and a shell to which the liner panel is mounted into a multiple of circumferential cavities.
5. The liner panel as recited in claim 4 , wherein the through aperture communicates airflow to balance the cooling airflow across one of the multiple of intermediate rails.
6. A liner panel for use in a combustor of a gas turbine engine, the liner panel comprising:
a perimeter rail that extends from a cold side of the liner panel, the perimeter rail formed by a forward circumferential rail, an aft circumferential rail, and axial rails that interconnect the forward and aft circumferential rails;
a multiple of intermediate rails within the perimeter rail, the multiple of intermediate rails extend from the cold side of the liner panel parallel to the axial rails between the forward circumferential rail and the aft circumferential rail, at least one of the multiple of intermediate rails includes a through aperture;
a dilution passage between two of the multiple of intermediate rails; and
at least one stud of a plurality of studs that extends from the cold side of the liner panel between each two of the multiple of intermediate rails;
wherein all of the plurality of studs are circumferentially offset from the multiple of intermediate rails.
7. The liner panel as recited in claim 6 , wherein the liner panel is an aft liner panel that surrounds a combustion chamber.
8. The liner panel as recited in claim 6 , wherein the liner panel is a forward liner panel that surrounds a combustion chamber.
9. The liner panel as recited in claim 6 , wherein the multiple of intermediate rails segment a cavity between the liner panel and a shell to which the liner panel is mounted into a multiple of axial cavities.
10. The liner panel as recited in claim 5 , wherein the through aperture communicates airflow to balance the cooling airflow across one of the multiple of intermediate rails.