Deflection mitigation structure for combustion system

A combustion section for a gas turbine engine includes 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 definesa second heat transfer coefficient less than the first heat transfer coefficient. 一种用于燃气涡轮发动机的燃烧区段包括内壳体，该内壳体包括限定压力容器的内径和第一传热系数的第一材料。第二材料至少部分地在第一材料的外径上延伸。第二材料径向设置在第一材料和燃烧器衬里之间。第二材料限定小于第一传热系数的第二传热系数。