Turbine shroud assembly with pinned attachment supplements for ceramic matrix composite component mounting

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

a carrier comprising metallic materials and arranged to extend circumferentially at least partway around an axis, the carrier including an outer wall, a first attachment flange extending radially inwardly away from the outer wall, and a second attachment flange extending radially inwardly away from the outer wall and being spaced apart from the first attachment flange, the first attachment flange and the second attachment flange being formed to include a first pin-receiving aperture extending only partway through the first attachment flange and the second attachment flange and the first attachment flange and the second attachment flange are arranged to open and face axially toward one another,

a blade track segment comprising ceramic matrix composite materials, the blade track segment including a shroud wall and a mount post that extends radially away from the shroud wall, the mount post arranged to lie axially between the first attachment flange and the second attachment flange and being formed to include a second pin-receiving aperture that extends axially through the mount post, and

a mount assembly configured to couple the blade track segment with the carrier, the mount assembly including a first replaceable grommet coupled to an axially-forward side of the mount post, a second replaceable grommet coupled to an axially-aft side of the mount post, and an attachment pin, each replaceable grommet extends axially at least partway into the second pin-receiving aperture to fix each replaceable grommet with the mount post, and the attachment pin is arranged within the first pin-receiving aperture and each grommet to couple the mount post of the blade track segment with the carrier so that each replaceable grommet provides a replaceable, sacrificial layer between the attachment pin and the mount post to reduce wear between the mount post and the attachment pin,

wherein the attachment pin extends axially between a first end and a second end and has an outer surface that is continuously cylindrical and without threads from the first end to the second end, and

wherein the first replaceable grommet and the second replaceable grommet are each press-fit with the mount post and with the attachment pin to provide an interference fit between the each replaceable grommet and the mount post and between each replaceable grommet and the attachment pin.

2. The turbine shroud assembly of claim 1 , wherein each replaceable grommet comprises a material selected from at least one of a silicon-carbide based composite, an oxide-based composite, a monolithic ceramic, and a metallic-based material with a ceramic-compatible coating.

3. The turbine shroud assembly of claim 1 , wherein each replaceable grommet includes a body arranged in the second pin-receiving aperture formed in the mount post of the blade track segment and a flange that engages an axially-facing surface of the mount post of the blade track segment.

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

a carrier comprising metallic materials and arranged to extend circumferentially at least partway around an axis, the carrier including a forward carrier member, an aft carrier member separate from the forward carrier member, and a mount pin that extends radially inward through apertures formed in the forward carrier member and the aft carrier member to couple the forward carrier member to the aft carrier member, the forward carrier member and the aft carrier member each comprising an outer wall and an attachment flange extending radially inward away from the outer wall, each attachment flange being formed to include a first pin-receiving aperture extending only partway through each attachment flange and arranged to open and face axially toward one another,

a blade track segment comprising ceramic matrix composite materials, the blade track segment including a shroud wall and a mount post that extends radially away from the shroud wall, the mount post arranged to lie axially between the attachment flanges and being formed to include a second pin-receiving aperture that extends axially through the mount post, and

a mount assembly configured to couple the blade track segment with the carrier, the mount assembly including a replaceable grommet and an attachment pin, the replaceable grommet extends axially at least partway into the second pin-receiving aperture to fix the replaceable grommet with the mount post and the attachment pin is arranged within the first pin-receiving aperture and the grommet to couple the mount post of the blade track segment with the carrier,

wherein the attachment pin extends axially between a first end and a second end and has an outer surface that is continuously cylindrical and without threads from the first end to the second end,

wherein the replaceable grommet has an inner surface engaged with the attachment pin and the inner surface has a constant diameter along an axial length of the replaceable grommet, and

wherein the replaceable grommet is each press-fit with the mount post and with the attachment pin to provide an interference fit between the replaceable grommet and the attachment pin and between the replaceable grommet and the mount post.

5. The turbine shroud assembly of claim 4 , wherein the grommet comprises a material selected from at least one of a silicon-carbide based composite, an oxide-based composite, a monolithic ceramic, and a metallic-based material with a ceramic-compatible coating.

6. The turbine shroud assembly of claim 4 , wherein the grommet includes a body arranged in the second pin-receiving aperture formed in the mount post of the blade track segment and a flange that engages an axially-facing surface of the mount post of the blade track segment.