Patent ID: 8955304
Filing Date: 2015-02-17
Classification: F02C,F02K,F05D,Y10T

Abstract:
1. A gas turbine engine comprising: a propulsion unit including a fan, and a free turbine connected to drive said fan about a first axis; a plurality of core engines, said core engines including at least a compressor, a combustion section, and a turbine, said core engine turbine connected to drive said compressor, and said compressor and said core engine turbine rotating about axis non-coaxial to said first axis; said plurality of core engines having an output from said core engine turbines passing over said free turbine; and said propulsion unit being positioned forwardly, and toward and inlet of the gas turbine engine relative to said core engines, and said core engines spaced rearwardly of the propulsion unit, and being separate from said propulsion unit.