Deflection Mitigation Structure for Combustion System
AssigneeGeneral Electric Company
InventorsAnthony Joseph Venzon, Jeremy Kevin Payne, Narendra Kumar Patel
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Abstract
A combustion section for a gas turbine engine including an inner casing comprising a first material defining an inner diameter of a pressure vessel and a first heat transfer coefficient. A second material is extended at least partially over an outer diameter of the first material. The second material is disposed radially between the first material and a combustor liner. The second material defines a second heat transfer coefficient less than the first heat transfer coefficient.
Claims20
A combustion section for a gas turbine engine, the combustion section comprising:
- an inner casing comprising a first material defining an inner diameter of a pressure vessel and a first heat transfer coefficient, wherein a second material is extended at least partially over an outer diameter of the first material, and wherein the second material is disposed radially between the first material and a combustor liner, and further wherein the second material defines a second heat transfer coefficient less than the first heat transfer coefficient.
A method for reducing a thermal gradient between an inner casing of a combustion section and a surrounding outer casing, the method comprising:
- forming a second material over an outer diameter of a first material defining the inner casing and a first heat transfer coefficient, wherein the second material defines a second heat transfer coefficient less than the first heat transfer coefficient.
Dependencies are inferred from the claim text.