Combustor panel for gas turbine engine
A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers are applied to the first substrate surface of the substrate layer. The one or more coating layers have a constant coating layer thickness and the substrate layer thickness tapers along an axial length of the heat shield panel.
1. A heat shield panel assembly for a gas turbine engine, comprising a first heat shield panel and a second heat shield panel, each of the first heat shield panel and the second heat shield panel including:
a substrate layer including:
a first substrate surface; and
a second substrate surface opposite the first substrate surface, the first substrate surface and the second substrate surface defining a substrate layer thickness therebetween; and
one or more thermally protective coating layers applied to the first substrate surface of the substrate layer;
wherein the substrate layer thickness decreases to a tapered thickness at an upstream end of the heat shield panel over a taper length;
wherein the one or more coating layers have a constant coating layer thickness along the taper length; and
wherein the first heat shield panel is tapered at an overlap to the second heat shield panel.
2. The heat shield panel of claim 1 , wherein the taper length is equal to up to 50 percent of a heat shield panel length.
3. The heat shield panel of claim 2 , wherein the taper length is between 10 percent and 40 percent of the heat shield panel length.
4. The heat shield panel of claim 1 , wherein a taper angle between the first substrate surface and the second substrate surface is up to sixty degrees.
5. The heat shield panel of claim 1 , wherein the substrate layer is formed from a metallic material.
6. The heat shield panel of claim 1 , wherein at least one coating layer of the one or more coating layers is formed from a ceramic material.
7. The heat shield panel of claim 1 , further comprising a plurality of heat dissipation features extending from the second substrate surface.
8. The heat shield panel of claim 7 , wherein the plurality of heat dissipation features include one or more of pins or fins.
9. A combustor for a gas turbine engine, comprising:
a combustor shell; and
a plurality of heat shield panels secured to the combustor shell, the heat shield panels including:
a substrate layer including:
a first substrate surface; and
a second substrate surface opposite the first substrate surface, the first substrate surface and the second substrate surface defining a substrate layer thickness therebetween; and
one or more thermally protective coating layers applied to the first substrate surface of the substrate layer;
wherein the substrate layer thickness decreases to a tapered thickness at an upstream end of the heat shield panel over a taper length;
wherein the one or more coating layers have a constant coating layer thickness along the taper length; and
wherein a first heat shield panel of the plurality of heat shield panels is tapered at an overlap to a second heat shield panel of the plurality of heat shield panels.
10. The combustor of claim 9 , wherein the overlap defines a flow passage for a cooling airflow.
11. The combustor of claim 9 , wherein the taper length equals to up to 50 percent of a heat shield panel length.
12. The combustor of claim 11 , wherein the taper length is between 10 percent and 40 percent of the heat shield panel length.
13. The combustor of claim 9 , wherein a taper angle between the first substrate surface and the second substrate surface is up to sixty degrees.
14. The combustor of claim 9 , wherein the substrate layer is formed from a metallic material.
15. The combustor of claim 9 , wherein at least one coating layer of the one or more coating layers is formed from a ceramic material.
16. The combustor of claim 9 , further comprising a plurality of heat dissipation features extending from the second substrate surface.
17. The combustor of claim 16 , wherein the plurality of heat dissipation features include one or more of pins or fins.
18. A gas turbine engine, comprising:
a turbine; and
a combustor operably connected to the turbine, the combustor including:
a combustor shell; and
a plurality of heat shield panels secured to the combustor shell, the heat shield panels including:
a substrate layer including:
a first substrate surface; and
a second substrate surface opposite the first substrate surface, the first substrate surface and the second substrate surface defining a substrate layer thickness therebetween; and
one or more thermally protective coating layers applied to the first substrate surface of the substrate layer;
wherein the substrate layer thickness decreases to a tapered thickness at an upstream end of the heat shield panel over a taper length;
wherein the one or more coating layers have a constant coating layer thickness along the taper length; and
wherein a first heat shield panel of the plurality of heat shield panels is tapered at an overlap to a second heat shield panel of the plurality of heat shield panels.