Compact advanced passive tip clearance control

摘要

A section of a gas turbine engine includes a rotor blade designed to rotate about an axis. The section also includes a case positioned radially outward from the rotor blade and extending circumferentially about the axis. The section also includes a control ring being annular, positioned radially inward from the case and designed to move radially relative to the case. The section also includes a segmented blade outer air seal (BOAS) including a plurality of BOAS segments each being positioned radially outward from the rotor blade, movably coupled to the control ring, and designed to move circumferentially relative to each other such that a circumferential gap between each of the plurality of BOAS segments changes in size in response to a temperature change in the section of the gas turbine engine.