CMC component with structure for directing cooling air flow

A method of cooling a CMC component, the method comprising:

• providing a CMC component comprising:
• a base having a radial outer surface and a radial inner surface, the base comprising a plurality of ceramic fiber plies and a ceramic matrix, and
• a forward flange structure and an aft flange structure each extending from the radial outer surface of the base, the forward flange structure having a first opening and a second opening, and the aft flange structure having a first opening and a second opening, and
• providing a first attachment pin and a second attachment pin for attaching the CMC component to a support structure, the first attachment pin passing through the first opening of the forward flange structure and the first opening of the aft flange structure, and the second attachment pin passing through the second opening of the forward flange structure and the second opening of the aft flange structure,
• wherein each of the attachment pins comprises an elongated body with a longitudinal axis extending from a first end to a second end, a cooling passageway extending axially from the first end along the longitudinal axis, and one or more cooling air outlets extend radially from the cooling air passageway to provide for discharge of fluid from the cooling passageway, and
• wherein the base further comprises at least one cooling cavity that extends from the radial outer surface of the base into an interior region of the base, the at least one cooling cavity having a cavity opening at the radial outer surface of the base, the at least one cooling cavity being defined by cavity side walls and a cavity bottom wall, and wherein the one or more cooling air outlets direct cooling air towards the at least one cooling cavity.

A turbine engine comprising:

• a fan section, a compressor section, a combustion chamber, and a turbine section, the turbine section includes at least one rotor and one or more turbine blade(s) extending radially outwardly from the at least one rotor;
• a blade outer air seal assembly positioned between the one or more turbine blade(s) and an outer casing to the engine;
• wherein the blade outer air seal assembly is formed of a plurality of blade outer air seal segments, wherein each blade outer air seal segment comprises:
• a base having a radial outer surface and a radial inner surface, the base comprising a plurality of ceramic fiber plies and a ceramic matrix,
• a forward flange structure and an aft flange structure each extending from the radial outer surface of the base, the forward flange structure having a first opening and a second opening, and the aft flange structure has a first opening and a second opening, and
• a first attachment pin and a second attachment pin for attaching the CMC component to a support structure, the first attachment pin passing through the first opening of the forward flange structure and the first opening of the aft flange structure, and the second attachment pin passing through the second opening of the forward flange structure and the second opening of the aft flange structure,
• wherein each of the attachment pins comprises an elongated body with a longitudinal axis extending in an axial direction from a first end to a second end, a cooling passageway extending axially from the first end along the longitudinal axis, and one or more cooling air outlets extend radially from the cooling air passageway to provide for discharge of fluid from the cooling passageway, and
• wherein the base further comprises at least one cooling cavity that extends from the radial outer surface of the base into an interior region of the base, the at least one cooling cavity having a cavity opening at the radial outer surface of the base, the at least one cooling cavity being defined by cavity side walls and a cavity bottom wall, and wherein the one or more cooling air outlets direct cooling air towards the at least one cooling cavity.