CPC F01D 25/08 (2013.01) [F05D 2220/32 (2013.01); F05D 2240/60 (2013.01); F05D 2300/614 (2013.01)] | 12 Claims |
1. A gas turbine engine comprising:
a plurality of rotating components housed within a compressor section and a turbine section;
a first tap connected to said compressor section and configured to deliver air at a first pressure;
a heat exchanger connected downstream of said first tap;
a rotating surface radially outward of a non-rotating surface defining a flowpath therebetween and wherein the non-rotating surface faces the rotating surface, wherein the flowpath is connected downstream of said heat exchanger and is configured to deliver air to at least one of said plurality of rotating components, wherein at least a portion of said non-rotating surface and said rotating surface comprising a base metal;
an insulation material disposed on a surface along the flowpath;
wherein said insulation material being provided outwardly of said base metal on at least a portion of said non-rotating surface; and
wherein said insulation material on said non-rotating surface includes a ceramic fiber blanket formed of bulk fibers, wherein said base metal is radially inward of said ceramic fiber blanket and an outer wall is attached on an opposed radial side of said ceramic fiber blanket relative to said base metal, and wherein said non-rotating surface, said ceramic fiber blanket and said outer wall form a non-rotating structure.
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