Combustor panel stud cooling effusion through heat transfer augmentors
A gas turbine engine component having a first surface in communication with a core airflow. The gas turbine engine component further includes a second surface, different than the first surface, for cooling the first surface. The gas turbine engine component further includes a heat transfer augmentor extending from the second surface. The gas turbine engine component further includes a heat transfer augmentor effusion hole extending through the gas turbine engine component from a sidewall of the heat transfer augmentor to the first surface.
1. A gas turbine engine component comprising:
a first surface in communication with a core airflow;
a second surface, different than the first surface, for cooling the first surface;
a heat transfer augmentor extending from the second surface;
a heat transfer augmentor effusion hole extending through the gas turbine engine component from a sidewall of the heat transfer augmentor to the first surface; and
a stud configured to secure a second gas turbine engine component to the gas turbine engine component, wherein an outlet of the heat transfer augmentor effusion hole at least partially overlaps with a projection of the stud on the first surface, the projection being projected through the second surface to the first surface.
2. The gas turbine engine component of claim 1 , wherein the heat transfer augmentor has a height extending from the first surface to the second surface, a length extending in a direction from the heat transfer augmentor to the stud, and a width that is greater than the length.
3. The gas turbine engine component of claim 1 , wherein the heat transfer augmentor includes multiple heat transfer augmentors surrounding the stud.
4. The gas turbine engine component of claim 3 , wherein the heat transfer augmentor effusion hole includes multiple effusion holes each extending through the first surface and portions of respective heat transfer augmentors.
5. The gas turbine engine component of claim 1 , wherein the heat transfer augmentor effusion hole has an inlet located on the heat transfer augmentor and the outlet in a combustion chamber.
6. The gas turbine engine component of claim 1 , further comprising at least one panel effusion hole extending through the gas turbine engine component from the second surface to the first surface.
7. The gas turbine engine component of claim 6 , wherein the heat transfer augmentor effusion hole extends at a first angle relative to a plane defined by a surface of the first surface, wherein the at least one panel effusion hole extends at a second angle relative to the plane, and wherein the first angle is different from the second angle.
8. A combustor panel for a gas turbine engine, the combustor panel comprising:
a first surface configured to at least partially define a combustion chamber;
a second surface, different than the first surface, for cooling the first surface;
a heat transfer augmentor configured to extend from the second surface;
a heat transfer augmentor effusion hole extending through the combustor panel from a sidewall of the heat transfer augmentor to the first surface; and
a stud configured to secure a shell to the combustor panel, wherein an outlet of the heat transfer augmentor effusion hole at least partially overlaps with a projection of the stud on the first surface, the projection being projected through the second surface to the first surface.
9. The combustor panel of claim 8 , wherein the heat transfer augmentor includes at least one of a stub, a pin, or a rail.
10. The combustor panel of claim 8 , wherein the heat transfer augmentor has an oblong cross-section.
11. The combustor panel of claim 10 , wherein the heat transfer augmentor effusion hole includes multiple effusion holes each extending through respective heat transfer augmentors to the first surface.
12. The combustor panel of claim 8 , wherein the heat transfer augmentor effusion hole has an inlet located on the heat transfer augmentor and the outlet in the combustion chamber.
13. The combustor panel of claim 8 , further comprising at least one panel effusion hole extending through the gas turbine engine component from the second surface to the first surface.
14. The combustor panel of claim 13 , wherein the heat transfer augmentor effusion hole extends at a first angle relative to a plane defined by a surface of the first surface, wherein the at least one panel effusion hole extends at a second angle relative to the plane, and wherein the first angle is different from the second angle.
15. The combustor panel of claim 8 , wherein the heat transfer augmenter includes multiple heat transfer augmentors surrounding the stud.
16. A combustor liner for use in a combustor section of a gas turbine engine, the combustor liner comprising:
a panel configured to at least partially define a combustion chamber;
a shell;
a heat transfer augmentor configured to extend from the panel to the shell and define a heat transfer augmentor height, the heat transfer augmentor height being equal to a gap between the panel and the shell;
a pin effusion hole extending through the panel and a portion of the heat transfer augmentor to port a compressed gas through the panel and the portion of the heat transfer augmentor to the combustion chamber; and
a stud configured to secure the panel to the shell, wherein an outlet of the pin effusion hole at least partially overlaps with a projection of the stud through the panel.
17. The combustor liner of claim 16 , wherein the heat transfer augmenter has a length extending in a direction from the heat transfer augmentor to the stud, and a width that is greater than the length.