METHOD OF USAGE OF FUEL FROM AIRCRAFT FUEL SYSTEM, FUEL SYSTEM (TWO VERSIONS) AND ITS SERVICE TANK Russian patent published in 2008 - IPC B64D37/00 

FIELD: aeronautical engineering; aircraft fuel systems; methods of usage of fuel from aircraft fuel systems.

SUBSTANCE: proposed fuel system includes fuel tank located in center-wing section and three tanks located in succession along each outer wing panel: first tank is located near center-wing panel; second tank is located in peripheral section of center-wing panel and third tank which is divided into main and service compartments is located in middle section. Method of usage of fuel consists in the following procedure: first, fuel is used from tank located in center-wing section, after which fuel is used from tanks located near center-wing section and then from tanks located in peripheral section of outer wing panels and finally from middle section of outer wing panels. Usage of fuel is accompanied by inter-tank transfer of fuel when fuel from all tanks is transferred to tanks located in middle section of wing. Excessive fuel from middle section tanks is successively re-transferred to peripheral tanks of wing, as well as to tanks located near center-wing panel and to center-wing panel tank. Fuel transfer is carried out by pumping or pouring fuel under action of gravitational forces. Proposed fuel system includes fuel transfer lines, upper and lower overflow passages which are used for inter-tank transfer of fuel. According to the first version, fuel from all tanks is transferred to main compartments of tanks which are located in middle section of wing and then fuel from these compartments is transferred to service compartments. According to the second version, fuel from all tanks is transferred directly to service tanks of system. Service compartment is provided with fluid medium sprayers which make it possible to separate gaseous inclusions from liquid fuel fed to service compartment. Separated gaseous inclusions are evacuated to adjacent tank of system. Proposed method of usage of fuel makes it possible to minimize action of bending moment on outer wing panels, change in aircraft in-flight CG position, reduction of fuel system mass and remaining unusable fuel. Proposed method provides for simplified control of fuel usage and separation of fuel into liquid and gaseous phases at evacuation of separated gaseous phase beyond service compartment boundaries.

EFFECT: enhanced efficiency.

17 cl, 22 dwg