Patent ID: 11913348
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 6:
7. A gas turbine engine comprising:
a compressor section, a combustor section and a turbine section, said turbine section having alternating rows of rotating turbine blades, and rows of stator vanes, with at least one row of said stator vanes being formed of ceramic matrix composite materials;
said stator vanes having a stator vane body having an airfoil with a leading edge, a trailing edge, a suction side and a pressure side, and having at least one internal cooling channel, said stator vane body being formed of ceramic matrix composite materials;
a spar received within said at least one internal cooling channel and formed of a metal, and said spar having an outer peripheral surface spaced from an inner peripheral surface of the at least one internal cooling channel to define a cooling air path, with said cooling air path having a varying cross-sectional area through the at least one internal cooling channel;
the varying cross-sectional area being achieved by a plurality of enlarged portions extending from the outer peripheral surface of the spar or an inner peripheral surface of the stator vane body, and said stator vane body inner periphery being spaced from said spar outer periphery at said enlarged portion such that the cooling air path extends along said plurality of enlarged portions; and
wherein said plurality of enlarged portions are achieved by said spar having a variation in said outer surface with there being a thinner portion leading into an outwardly ramped portion at each of said leading edge, said trailing edge, a suction wall face and a pressure wall face of said spar to change the cross-sectional area.