FIELD: physics.
SUBSTANCE: invention relates to aircraft fuel systems. The fuel system comprises supply tanks (1, 2) inside of which there are pumps (3, 4), fuel supply pipes, where check valves (9, 10) and fire-proof taps (13, 14) are installed, as well as cross-feeding taps (18, 21). Cross-feeding is in form of two connected pipes (19, 22), each connecting the check-valve (17, 20) and the cross-feed tap (18, 21), wherein the check valve is located with respect to the cross-feed tap so that fuel supply via the connecting pipe is possible only when the cross-feed tap is open.
EFFECT: invention provides safe separate fuel supply of engines.
1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| HELICOPTER | 1993 |
|
RU2102285C1 |
| FUEL TRANSFER SYSTEM | 0 |
|
SU593405A1 |
| FLYING VEHICLE FUEL SYSTEM | 1995 |
|
RU2082653C1 |
| FUEL SUPPLY SYSTEM OF GAS TURBINE ENGINE | 2008 |
|
RU2364738C1 |
| AIRCRAFT FUEL SYSTEM | 2005 |
|
RU2287458C1 |
| HELICOPTER FUEL SYSTEM | 1992 |
|
RU2027641C1 |
| PLANE FUEL SYSTEM | 2006 |
|
RU2323857C1 |
| FUEL SYSTEM OF MULTIENGINED AIRCRAFT | 1990 |
|
SU1802494A1 |
| FLYING VEHICLE FUEL-FEED SYSTEM | 0 |
|
SU626535A1 |
| ENGINE CRYOGENIC FUEL FEED SYSTEM | 1998 |
|
RU2192989C2 |
