US Patent 10364696 Mechanism and method for rapid response clearance control

A clearance control assembly for providing clearance control between a blade outer air seal and an airfoil tip of a gas turbine engine includes an outer case, a first blade outer air seal carrier, a blade outer air seal, an actuator, a load-applying member, and a lever. The first blade outer air seal carrier is positioned radially inward of the outer case. The blade outer air seal is positioned radially inward of and mounted to the blade outer air seal carrier. The load-applying member is positioned to be acted upon by the actuator during operation of the actuator. The lever is connected to the case and is operably in contact with the load-applying member and the first blade outer air seal carrier.