FUEL SYSTEM FOR HELICOPTER WITH JET ENGINES AT BLADES Russian patent published in 2015 - IPC B64C27/18 F02C7/22 

FIELD: aircraft engineering.

SUBSTANCE: proposed fuel system comprises fuel tank (1) with booster pump (2), fuel line (3) arranged partly inside rotor shaft and blades. Fuel line of every blade is provided with rotor rpm controller. Electrically driven starting and low-rpm pump (5) is arranged at fuel line section downstream of booster pump with outlets in number corresponding to that of engines (8) and engine working condition control pump (7) driven by rotor shaft (11) via gearing (12) of gearbox (10). Fuel manifold (15) is arranged at inlet of blade (14) fuel lines (9) to transfer fuel from fixed fuel line sections to their moving sections (9′) in every blade (14). Fuel manifold (15) consists of two compartments (16, 17). Fixed compartment (16) is secured at fixed pipe (13) inside rotor shaft (11). Moving compartment (17) is fitted on rotor shaft (11) and has circular chambers (18, 19) for fuel transfer.

EFFECT: possibility to rule out inertia of fuel feed and to effect the fuel pressure control.

3 cl, 2 dwg