Carlson, Gaskey & Olds, P.C.
Gas turbine engine having section with thermally isolated area
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a first compressor having a first overall pressure ratio, and a second compressor having a second overall pressure ratio. A ratio of the first overall pressure ratio to the second overall pressure ratio is greater than or equal to about 2.0. Further, a section of the gas turbine engine includes a thermally isolated area.
UNITED TECHNOLOGIES CORPORATION
F F F F F F F F F F
F05D F01D F01D F05D F01D F02C F02C F01D F02C F05D
additional inventional inventional additional inventional inventional inventional inventional inventional additional
Brian D. James D. Gabriel L.
Merry Hill Suciu