Ceramic matrix composite blade track assembly with tip clearance control

A blade track assembly adapted for use around a turbine wheel in a gas turbine engine, the assembly comprising

• a plurality of blade track segments made from ceramic matrix composite materials, the plurality of blade track segments including a first segment and a second segment each shaped to include a runner that extends partway around a central axis to define a primary gas path and a hanger-receiving slot arranged to open facing circumferentially around the central axis, and
• a tip clearance control system configured to move the plurality of blade track segments radially inward and outward relative to the central axis, the tip clearance control system including a first hanger that is slidably received within the hanger-receiving slot of the first segment and is slidably received within the hanger-receiving slot of the second segment so that the first segment and the second segment are mounted for movement circumferentially toward and away from one another in response to radially outward and inward movement of the hanger,
• wherein the first hanger includes a radially-extending trunk that extends radially between a first terminal end and a second terminal end, a first leg that extends circumferentially from the second end of the radially-extending trunk into the hanger-receiving slot of the first segment, and a second leg that extends circumferentially from the second end of the radially-extending trunk opposite the first leg into the hanger-receiving slot of the second segment, and the radially-extending trunk, the first leg, and the second leg are fixed together for movement as a unit,
• wherein the tip clearance control system includes a second hanger discrete from and spaced apart circumferentially from the first hanger and is slidably received within the hanger-receiving slot of the second segment.

A gas turbine engine comprising

• a compressor configured to receive and compress air for discharge at a pressure greater than when received, and
• a turbine including a turbine wheel having blades mounted for rotation about a central axis and a blade track assembly that extends around the blades to block hot gasses from moving over the blades without interacting with the blades, the blade track assembly including a plurality of blade track segments made from ceramic matrix composite materials that define a primary gas path around the turbine wheel and a tip clearance control system configured to move the plurality of blade track segments radially inward and outward to control a gap defined between the blades and the plurality of blade track segments during operation of the gas turbine engine,
• wherein the plurality of blade track segments includes (i) a first segment shaped to include a runner that extends partway around the central axis and a hanger-receiving slot arranged to open facing circumferentially around the central axis and (ii) a second segment shaped to include a runner that extends partway around the central axis and a hanger-receiving slot arranged to open facing the hanger-receiving slot of the first segment, and
• wherein the tip clearance control system includes a metallic case that extends around the central axis radially outward of the plurality of blade track segments and a hanger coupled to the metallic case that extends radially inward to the plurality of blade track segments and into the hanger receiving slots of the first segment and the second segment,
• wherein the hanger includes a radially-extending trunk that extends radially between a first end and a second end, a first leg that extends circumferentially from the second end of the radially-extending trunk, and a second leg that extends circumferentially from the second end of the radially-extending trunk opposite the first leg, and the hanger is pivotably mounted to the metallic case at the first end of the radially-extending trunk such that the radially-extending trunk, the first leg, and the second leg pivot together.