Turbine shroud assembly with dovetail retention system

A turbine shroud assembly for use with a gas turbine engine, the turbine shroud assembly comprising

• a turbine outer case including a forward outer case and an aft outer case, the forward outer case including a forward outer wall, a forward mount flange extending radially outward from the outer wall at an aft terminating end of the forward outer wall, and a radially inward extended forward hanger, the aft outer case including an aft outer wall, an aft mount flange extending radially outward from the aft outer wall at a forward terminating end of the aft outer wall, and a radially inward extending aft hanger,
• a carrier assembly made of metallic material and arranged circumferentially around an axis, the carrier assembly comprising a forward carrier segment and an aft carrier segment, the forward carrier segment including a forward radially extending flange that couples with the forward hanger and a forward load carrying portion that extends axially aft from an inner end of the forward extending flange, the aft carrier segment including a forward flange that couples with the aft hanger, an outer wall that extends axially aft from the forward flange, an aft flange that extends radially inward from an aft end of the outer wall, and an aft load carrying portion that extends axially forward from an inner end of the aft flange, and
• a blade track segment made of ceramic matrix composite materials, the blade track segment including an arcuate runner that extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner to couple with the carrier assembly, the attachment feature includes radially inward facing and angled load surfaces that engage the forward load carrying portion of the forward carrier segment and the aft load carrying portion of the aft carrier segment, and a radially outward facing locating surface,
• wherein the forward carrier segment and the aft carrier segment urge the angled load surfaces to be pushed radially outward by the forward and aft load carrying portions, resulting in the locating surface of the attachment feature to bias towards the outer wall of the aft carrier segment thereby radially locating the blade track segment relative to the carrier assembly, and the forward carrier segment and the aft carrier segment are clamped together in compression so that the blade track segment does not move radially relative to the axis in response to thermal growth of the turbine shroud assembly.

A method comprising

• providing a turbine outer case arranged circumferentially around an axis, a blade track segment, and a carrier, the turbine outer case having a first case and a second case, the blade track segment including an arcuate runner that extends circumferentially partway around the axis and an attachment feature that extends radially outward from the runner, the attachment feature includes radially inward facing and angled load surfaces, and the carrier including a first carrier segment and a second carrier segment,
• aligning the attachment feature of the blade track segment with the first carrier segment and the second carrier segment,
• moving the first carrier segment and the second carrier segment relative to each other to trap the attachment feature between the first carrier segment and the second carrier segment so that load carrying portions included in the first carrier segment and the second carrier segment engage the radially inward facing and angled load surfaces of the attachment feature and move the radially inward facing and angled load surfaces radially outward,
• aligning the first case and the second case with flanges of the carrier, and
• moving the first case and the second case relative to each other to trap the flanges of the carrier between the first case and the second case so that the carrier is supported by the turbine outer case.