Clearance control for gas turbine engine section

A section of a gas turbine engine comprising:

• a case structure having a first coefficient of thermal expansion;
• a continuous ring-shaped liner having a second coefficient of thermal expansion that is substantially different than the first coefficient of thermal expansion;
• and
• a flexible leaf member having first and second portions mechanically affixed and secured respectively to the liner and to the case structure such that the first and second portions are respectively immovable with respect to the liner and to the case structure, the leaf member configured to accommodate diametrical change in the liner throughout various section operating temperatures, wherein the first and second portions are spaced from one another in a circumferential direction that corresponds to a blade rub direction.