Abstract: Aspects of the disclosure are directed to a system of an engine, comprising: a clearance control thermal ring, and a seal ring, where a radial gap with respect to an axial centerline of the engine is formed between a radial end of the clearance control thermal ring and a facing radial surface of the seal ring, where the clearance control thermal ring is made of a first material and the seal ring is made of a second material that is different from the first material, and where a first coefficient of thermal expansion of the first material is less than a second coefficient of thermal expansion of the second material.

Abstract: A joint for a gas turbine engine includes a first component, a second component, an annular shim disk, and fasteners. The first component has a first ring portion and a first annular radial flange that extends from the first ring portion. The second component has a second ring portion and a second annular radial flange that extends from the second ring portion. The first annular radial flange and the second annular radial flange are spaced apart by a gap that has a variable gap size that is subject to a stacking tolerance. The annular shim disk is disposed in the gap. The fasteners are secured through the first annular radial flange, the annular shim disk, and the second annular radial flange.

Abstract: Aspects of the disclosure are directed to a system of an engine, comprising: a clearance control thermal ring, and a seal ring, where a radial gap with respect to an axial centerline of the engine is formed between a radial end of the clearance control thermal ring and a facing radial surface of the seal ring, where the clearance control thermal ring is made of a first material and the seal ring is made of a second material that is different from the first material, and where a first coefficient of thermal expansion of the first material is less than a second coefficient of thermal expansion of the second material.