Carlson, Gaskey & Olds, P.C.
Advanced distributed engine architecture-design alternative
A gas turbine engine according to the present disclosure includes a first compressor and a first turbine for driving the first compressor. A core section includes a second compressor and a second turbine for driving the second compressor. A third turbine is arranged fluidly downstream of the first turbine and the second turbine and configured to drive a power take-off. A first duct system is arranged fluidly between the low-pressure compressor and the core section. The first duct system is arranged to reverse fluid flow before entry into the core section.
Raytheon Technologies Corporation
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additional inventional additional inventional inventional
Joseph B. Jeffery F. Frederick M. James D. Gabriel L.
Staubach Perlak Schwarz Hill Suciu