Turbine shroud with containment features

A turbine shroud adapted for use in a gas turbine engine, the turbine shroud comprising

• a first turbine shroud segment including a first carrier arranged to extend circumferentially at least partway about a center axis, a first blade track segment, and a first intermediate carrier configured to couple the first blade track segment to the first carrier, wherein the first blade track segment formed to include a first runner shaped to extend circumferentially partway around the center axis and a first attachment portion that extends radially outward from the first runner, and
• a second turbine shroud segment arranged circumferentially adjacent to the first turbine shroud segment, the second turbine shroud segment including a second carrier arranged to extend circumferentially at least partway about the center axis, a second blade track segment, and a second intermediate carrier configured to couple the second blade track segment to the second carrier, wherein the second blade track segment formed to include a second runner shaped to extend circumferentially partway around the center axis and a second attachment portion that extends radially outward from the second runner,
• wherein the first intermediate carrier is shaped to include a first intermediate carrier body coupled with the first attachment portion of the first blade track segment, a plurality of first retainers that extend radially and couple the first carrier with the first intermediate carrier body, and a flange that extends circumferentially from a circumferential end the first intermediate carrier body and engages an adjacent circumferential end of a second intermediate carrier body included in the second intermediate carrier to form an overlap therebetween.

A method comprising

• providing a first turbine shroud segment including a first carrier, a first blade track segment, and a first intermediate carrier, the first blade track segment including a first runner shaped to extend partway around an axis, a first fore mount post that extends radially outward from the first runner, and a first aft mount post spaced apart axially from the first fore mount post that extends radially outward from the first runner, and the first intermediate carrier including a first intermediate carrier body, a flange that extends circumferentially from a circumferential end of the first intermediate carrier body, and pins,
• providing a second turbine shroud segment including a second carrier, a second blade track segment, and a second intermediate carrier, the second blade track segment including a second runner shaped to extend partway around the axis, a second fore mount post that extends radially outward from the second runner, and a second aft mount post spaced apart axially from the second fore mount post that extends radially outward from the second runner, and the second intermediate carrier including a second intermediate carrier body and pins,
• arranging the first intermediate carrier body axially between the first fore mount post and the first aft mount post of the first blade track segment,
• inserting the pins axially through the first fore mount post, the first intermediate carrier body, and the first aft mount post to couple the first blade track segment to the first intermediate carrier body,
• arranging the first intermediate carrier in an attachment space formed in the first carrier,
• coupling the first intermediate carrier with the first carrier,
• arranging the second intermediate carrier body axially between the second fore mount post and the second aft mount post of the second blade track segment,
• inserting the pins axially through the second fore mount post, the second intermediate carrier body, and the second aft mount post to couple the second blade track segment to the second intermediate carrier body,
• arranging the second intermediate carrier in an attachment space formed in the second carrier,
• coupling the second intermediate carrier with the first carrier, and
• arranging the second turbine shroud segment circumferentially adjacent to the first turbine shroud segment in the gas turbine engine so that the flange of the first intermediate carrier engages an adjacent circumferential end of the second intermediate carrier body to form an overlap therebetween.