Gas turbine engine rapid response clearance control system with air seal segment interface

An active clearance control system of a gas turbine engine comprising:

• an air seal segment with a bridge hook having a lugged aperture;
• and
• a puller with a multiple of circumferentially spaced lugs engageable with said lugged aperture,
• wherein the puller moves radially and radially moves said air seal segment,
• wherein said multiple of circumferentially spaced lugs each define a lug engagement surface engageable with a respective aperture engagement surface of said lugged aperture.

A method of active blade tip clearance control for a gas turbine engine, comprising:

• engaging a puller that includes a multiple of circumferentially spaced lugs with an air seal segment that includes a lugged aperture, wherein the puller moves radially and radially moves the air seal segment and said multiple of circumferentially spaced lugs each define a lug engagement surface engageable with a respective aperture engagement surface of said lugged aperture,
• inserting said multiple of circumferentially spaced lugs that extend from the puller into the lugged aperture;
• and
• rotating the puller to obtain a lugged contact interface that allows the air seal segment to move radially in response to radial movement of the puller.