Combustor wall having cooling element(s) within a cooling cavity
AssigneeUnited Technologies Corporation
InventorsFrank J. Cunha, Stanislav Kostka, JR.
Life of this patent
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Abstract
A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a cooling element. The shell defined a first set of apertures. The heat shield defines a second set of apertures. The cooling element extends between the shell and the heat shield within a tapered cooling cavity defined between the shell and the heat shield. The tapered cavity is fluidly coupled with the first and the second sets of apertures. The cooling element is thermally coupled to one of the shell and the heat shield.
Claims20
A combustor wall for a turbine engine, the combustor wall comprising:
- a shell defining a first set of apertures;
- a heat shield defining a second set of apertures;
- and
- a cooling element extending between the shell and the heat shield within a tapered cooling cavity defined between the shell and the heat shield,
- wherein the tapered cavity is fluidly coupled with the first and the second sets of apertures and the cooling element is thermally coupled to one of the shell and the heat shield.
A combustor for a turbine engine, the combustor comprising:
- a combustor shell defining a first set of apertures;
- a combustor heat shield defining a second set of apertures, the heat shield attached to the shell;
- and
- a cooling element, wherein the shell and the heat shield at least partially define a cooling cavity therebetween with the cooling element extending into the cooling cavity and the cooling cavity fluidly coupling the first and the second sets of apertures.
Dependencies are inferred from the claim text.