GAS TURBINE ENGINE HAVING SECTION WITH THERMALLY ISOLATED AREA

摘要

A gas turbine engine (20) according to an exemplary aspect of the present disclosure includes, among other things, a first compressor (44) having a first overall pressure ratio, and a second compressor (52) 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 (78).