Pin mounted ceramic matrix composite heat shields with impingement cooling

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

• a blade track segment made of ceramic matrix composite materials having a shroud wall that extends circumferentially partway around an axis and a first attachment flange and a second attachment flange that each extend radially outward from the shroud wall away from the axis, the second attachment flange spaced apart axially from the first attachment flange,
• a pin that extends parallel to the axis into a metallic support structure and through an aperture in at least one of the first attachment flange and/or the second attachment flange of the blade track segment so as to couple the blade track segment to the metallic support structure, the metallic support structure including a cooling air plenum, a first intermediate support wall that extends radially inward from an outer wall of the metallic support structure axially aft of the first attachment flange, and a second intermediate support wall that extends radially inward from the outer wall of the metallic support structure axially forward of the second attachment flange and spaced apart axially from the first intermediate support wall, and
• a cooling passageway formed in the metallic support structure, the cooling passageway formed in the metallic support structure and shaped to define an inlet and an outlet, the inlet of the cooling passageway offset from the outlet of the cooling passageway in a radial direction and in at least one of an axial direction relative to the axis or a circumferential direction relative to the axis such that a central axis of the cooling passageway extends though the cooling passageway and intersects a preselected cooling area on the radially extending wall of at least one of the first attachment flange and/or the second attachment flange and shaped to direct cooling air from the cooling air plenum and onto the preselected cooling area of the blade track segment.

A method comprising

• providing a blade track segment in a turbine shroud assembly, the blade track segment including a shroud wall shaped to extend partway around an axis and an attachment flange that that extends radially outward from the shroud wall,
• providing a pin that extends into a metallic support structure and through an aperture in the attachment flange of the blade track segment so as to couple the blade track segment to the metallic support structure,
• arranging the blade track segment adjacent to the metallic support structure,
• inserting the pin through a wall of the metallic support structure and the aperture of the attachment flange to couple the blade track segment to the metallic support structure,
• conducting a flow of cooling air through a passageway formed in the metallic support structure, and
• directing the flow of cooling air thorough a cooling passageway formed in the metallic support structure, the cooling passageway shaped to define an inlet and an outlet, the inlet of the cooling passageway offset from the outlet of the cooling passageway in a radial direction and in at least one of an axial direction relative to the axis or a circumferential direction relative to the axis such that a central axis of the cooling passageway extends though the cooling passageway and intersects a preselected cooling area on the radially extending wall of the attachment flange to direct cooling air onto the preselected cooling area of the attachment flange included in the blade track segment, the preselected cooling area located radially between the shroud wall and the pin as well as being circumferentially aligned with the pin so that heat absorbed by the shroud wall during use of the turbine shroud assembly is dissipated by the cooling air directed onto the preselected cooling area before being conducted to the pin so as to manage pin-deformation and pin-life.