FIELD: aircraft engineering.
SUBSTANCE: claimed aircraft comprises midflight gas turbine engine plant with at least two engines. Every said engine is composed of isolated root gas turbine engine with outer cowling, compressor, combustion chamber and compressor drive turbine, and propulsors located separately from said isolated root gas turbine engine. Outlet of compressor of every engine has a circular sorter for air bleed for propulsors to feed air portion created by the compressor to said combustion chamber and turbine compressor actuation. The other air high-pressure portion is forced in propulsor feed pipeline and to the other systems and hardware to maintain normal operation of the propulsor. Said isolated root engine are mounted at pylons under the wing while said propulsors composed of turbulence ejection propulsors are mounted at wing top surface. Circular sorter of every engine is connected to the pipe located in the pylon and, by opposite end, to propulsor feed pipeline arranged in the wing front section. Every pipe connecting the engine circular sorter is provided with check valve to prevent compressed air feed into failed engine.
EFFECT: fuel saving, lower noise, simplified design, decreased weight, higher flight safety.
4 dwg
