Ceramic matrix composite heat shield for use in a turbine vane and a turbine shroud ring

A turbine section of a gas turbine engine, the turbine section comprising

• a carrier segment comprising metallic materials and extending partway around a central axis of the gas turbine engine, the carrier segment including a main body having a forward side, an aft side, at least one vane portion, and at least one turbine shroud portion located axially adjacent to the at least one vane portion,
• a vane assembly including at least one support spar comprising metallic materials, the at least one support spar coupled to a corresponding vane portion of the at least one vane portion of the main body and extending radially inward from the main body of the carrier segment toward the central axis,
• a turbine shroud assembly including at least one turbine shroud located axially adjacent to the at least one vane, the turbine shroud including a corresponding turbine shroud portion of the at least one turbine shroud portion of the main body, and
• a heat shield comprising ceramic matrix composite materials included as part of the vane assembly and the turbine shroud assembly, the heat shield formed as a one piece component that is shaped to include (i) at least one vane having an outer platform and an airfoil that protect a corresponding support spar of the at least one support spar of the vane assembly, (ii) at least one seal segment portion that protects a corresponding turbine shroud portion of the at least one turbine shroud portion of the main body so as to provide the vane assembly and the turbine shroud assembly without a gap between the outer platform of the vane assembly and the turbine shroud assembly, and (iii) a forward turn-up extending radially outward from a forward edge of the heat shield and an aft turn-up extending radially outward from an aft edge of the heat shield, the forward turn-up and the aft turn-up coupling the heat shield to the carrier segment.

A method comprising

• providing a turbine case shaped to surround a central axis of a turbine section of a gas turbine engine,
• providing a carrier segment comprising metallic materials and extending partway around the central axis, the carrier segment including a main body coupled to the case, a forward shield mount arranged along a forward side of the main body, and an aft shield mount arranged along an aft side of the main body,
• providing a vane assembly including a support spar comprising metallic materials,
• coupling the support spar to the main body of the carrier segment such that the support spar extends radially inward from the main body of the carrier segment toward the central axis,
• providing a turbine wheel including a disk mounted for rotation about the central axis and a plurality of blades coupled to the periphery of the disk for rotation therewith about the central axis,
• providing a turbine shroud located co-axially with and radially outward of the turbine wheel to block gases moving along the primary gas path from moving over the blades of the turbine wheel without interacting with the turbine blades, the turbine shroud including a turbine shroud portion of the carrier segment,
• forming a heat shield comprising ceramic matrix composite materials as a one piece component that is shaped to include (i) a vane portion having an outer platform and an airfoil that protect the support spar of the vane assembly, (ii) a seal segment portion that protects the turbine shroud portion of the carrier segment so as to provide the vane assembly and the turbine shroud without a gap between the outer platform of the vane assembly and the turbine shroud, and (iii) a forward turn-up extending radially outward from a forward edge of the outer platform and an aft turn-up extending radially outward from an aft edge of the seal segment portion, the heat shield included as part of the vane assembly and the turbine shroud, and
• coupling the forward turn-up and the aft turn-up of the heat shield to the carrier segment.