Seal assembly for gas turbine engine

A gas turbine engine, comprising:

• an engine case extending along an engine axis;
• an array of blades rotatable about the engine axis;
• and
• an array of blade outer air seals distributed about the array of blades to bound a core flow path, each of the seals including a sealing portion that extends circumferentially between opposed mate faces and an engagement portion along each of the opposed mate faces, with the opposed mate faces arranged to define an intersegment gap;
• an array of circumferentially spaced apart mounting blocks each arranged between the engagement portion of adjacent pairs of the seals, each of the mounting blocks defining an aperture for receiving a fastener mechanically attached to the engine case to limit movement of the respective one of the seals relative to the engine case;
• and
• wherein at least one of the fastener and the mounting blocks defines a first cooling passage that delivers cooling flow at a location adjacent to the respective intersegment gap.

A method of sealing of a gas turbine engine, comprising:

• positioning a mounting block between mate faces of adjacent blade outer air seals;
• securing with a fastener the mounting block to an engine case, the fastener including a first cooling passage;
• and
• communicating cooling flow from the first cooling passage to a location adjacent to an intersegment gap defined by the mate faces.