Patent ID: 8001792
Filing Date: 2011-08-23
Classification: F01D,F02C,Y02T,Y10T

Abstract:
1. Apparatus for channeling combustion gases to a turbine in a gas turbine engine, the engine having a compressor for providing compressed air, a combustor for combusting fuel with the compressed air to provide combustion gases, and a radial inflow turbine having an inlet configured to receive the combustion gases, the turbine being rotatable about an axis for expanding the combustion gases to produce work, the apparatus comprising: a plurality of nozzle guide vanes each having opposed axial ends and an axially directed hole; a pair of spaced apart, ring-shaped sidewalls, the plurality of guide vanes being attached between the sidewalls in an angularly spaced relation relative to the turbine axis and oriented for receiving the combustion gases from the combustor and directing the gases into the turbine inlet, the sidewalls including axially directed apertures positioned in-line with the holes of the respective angularly spaced guide vanes; a pair of spaced apart supports configured to position the sidewalls and attached guide vanes therebetween and concentric with the turbine axis and adjacent the turbine inlet, at least one of the supports also being configured to be secured to the engine; and means for capturing the sidewalls and attached guide vanes between the supports to permit thermal expansion and/or contraction radial movement of the sidewalls and attached guide vanes relative to the supports during engine operation, wherein the capturing means includes a plurality of bolt assemblies extending axially through the ring supports, the apertures in the sidewalls, and the holes in the guide vanes, wherein the apertures and holes each have an internal dimension in the radial direction greater than an outer dimension of the bolt assembly, the internal dimension being sized to accommodate said relative sliding thermal expansion and/or contraction radial movement.