US 11,773,735 B2
Vane ring assembly with ceramic matrix composite airfoils
Michael J. Whittle, Derby (GB); Daniel Clark, Derby (GB); Carl Boettcher, Nottingham (GB); and David Wright, Loughborough (GB)
Assigned to Rolls-Royce plc
Filed by Rolls-Royce plc, London (GB)
Filed on Dec. 22, 2021, as Appl. No. 17/560,202.
Prior Publication US 2023/0193769 A1, Jun. 22, 2023
Int. Cl. F01D 9/04 (2006.01); F01D 25/00 (2006.01)
CPC F01D 9/041 (2013.01) [F01D 25/005 (2013.01); F05D 2220/32 (2013.01); F05D 2230/60 (2013.01); F05D 2240/12 (2013.01); F05D 2300/20 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A turbine vane assembly for use in a gas turbine engine comprises
a plurality of turbine vanes comprised of ceramic matrix composite materials and adapted to interact with hot gases flowing through a gas path of the gas turbine engine, the plurality of turbine vanes arranged around an axis of the gas turbine engine, wherein each turbine vane of the plurality of turbine vanes is spaced apart circumferentially from an adjacent turbine vane included in the plurality of turbine vanes relative to the axis,
a segmented inner vane support comprised of metallic materials, arranged radially inwardly of the plurality of turbine vanes, and extending partway circumferentially about the axis, the segmented inner vane support configured to receive force loads applied to the plurality of turbine vanes by the hot gases, and
an outer vane support comprised of metallic materials and configured to receive force loads applied to the plurality of turbine vanes by the hot gases, the outer vane support including a full-hoop outer support ring located radially outward of the plurality of turbine vanes so as to locate the plurality of turbine vanes radially between the segmented inner vane support and the full-hoop outer support ring, the full-hoop outer support ring extending entirely circumferentially about the axis, the outer vane support further including a plurality of discrete support spars coupled to the full-hoop outer support ring and extending radially inward from the full-hoop outer support ring through an interior cavity of a respective turbine vane of the plurality of turbine vanes,
wherein each discrete support spar of the plurality of discrete support spars includes a radially outer end including an outer spar platform, the outer spar platform of each discrete support spar of the plurality of discrete support spars includes a plurality of fastener holes formed therein,
wherein the full-hoop outer support ring includes an annular outer mount platform extending entirely circumferentially about the axis and formed to include a plurality of fastener holes formed therein that are aligned with the plurality of fastener holes of the outer spar platform of each discrete support spar, and
wherein a fastener is arranged within each fastener hole of the outer spar platform and the annular outer mount platform so as to couple the discrete support spar to the full-hoop outer support ring.