| CPC F01D 9/041 (2013.01) [F01D 5/284 (2013.01); F01D 9/042 (2013.01); F05D 2240/12 (2013.01); F05D 2240/80 (2013.01); F05D 2250/291 (2013.01); F05D 2260/30 (2013.01); F05D 2300/6033 (2013.01)] | 8 Claims |
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1. A turbine section for a gas turbine engine, comprising:
inner and outer diameter ceramic matrix composite (CMC) support rings that define a gaspath there between, each of the inner and outer diameter CMC support rings being monolithic and continuous,
CMC vane arc segments disposed in the gaspath and supported by the inner and outer diameter CMC support rings, each of the CMC vane arc segments including inner and outer platforms and an airfoil section there between, and
at least one retainer engaging the inner or outer diameter CMC support rings with the CMC vane arc segments to retain the CMC vane arc segments between the inner and outer diameter CMC support rings, the outer diameter CMC support ring defining an outer diameter support ring aft end and a first support ring flange extending radially-inwardly from the outer diameter support ring aft end, the first support ring flange serving as the at least one retainer and engaging an aft face of the outer platform.
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