Patent ID: 11952917
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 7:
8. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, the turbine section including:
a carrier having a doveslot,
vane multiplets each including,
first and second ceramic matrix composite (CMC) singlet vanes arranged circumferentially adjacent each other, each of the first and second CMC singlet vanes including an airfoil section and a platform at one end of the airfoil section, the platform defining forward and trailing platform edges and first and second circumferential side edges, and
a CMC overwrap conjoining the first and second CMC singlet vanes, the CMC overwrap including fiber plies that are fused to both the platform of the first CMC singlet vane and the platform of the second CMC singlet vane, the fiber plies defining a dovetail fitting with the doveslot to secure the vane multiplet to the carrier.