Importance

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Abstract

A transition exit frame (10) for supporting a transition (12) extending downstream from a combustor (14) to a turbine assembly (16) in a turbine engine (18) and including one or more transition exit frame inserts (20) configured to reduce thermal distortion created during operation of the turbine engine (18) is disclosed. The transition exit frame (10) may be formed from one or more transition exit frame bodies (22). The transition exit frame body (22) may be formed from a first material (24) having a first coefficient of thermal expansion. The transition exit frame insert (20) may form at least a portion of the transition exit frame body (22). The transition exit frame insert (20) may be formed from a second material (26) having a second coefficient of thermal expansion that is different than the first coefficient of thermal expansion of the first material (24) to reduce distortion within the transition exit frame body (22) during operation of the turbine engine (18).

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First Claim