FIELD: aircraft engine engineering. SUBSTANCE: unit has drain tank 1. Fuel ejector 4 is connected to intake opening 2 and inlet and outlet branch pipes of make-up pump 3. Cut-off valve 6 and check valve 7 are mounted in line 5 for discharging fuel. Overlapping member 8 of cut-off valve 6 has a servodrive constructed as diaphragm 9. Spring 11 is mounted inside control space 10 of the servodrive. The unit also has air ejector 12 whose active nozzle is connected to the compressor of the engine. The mixing chamber of the unit is connected with tank 1. The passive nozzle is in communication with control space 10 and with signal opening 14 of tank 1 through nozzle 13. Opening 14 is positioned above intake opening 2. EFFECT: improved design. 1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| FLYING VEHICLE FUEL SYSTEM | 1995 |
|
RU2082653C1 |
| DEVICE TO DELIVER FUEL TO STARTING NOZZLES | 1993 |
|
RU2095613C1 |
| CONTROL SYSTEM OF GAS TURBINE ENGINE | 1991 |
|
RU2008482C1 |
| GAS-TURBINE ENGINE FUEL DRAINAGE SYSTEM | 1998 |
|
RU2141049C1 |
| AIRCRAFT COMPARTMENT FUELLING SYSTEM | 1997 |
|
RU2140380C1 |
| GAS-TURBINE ENGINE GOVERNING SYSTEM | 1989 |
|
RU1732736C |
| LIQUID-PROPELLANT ROCKET ENGINE PLANT | 1998 |
|
RU2136935C1 |
| PROPELLANT TANK (FUEL AND OXIDIZER TANKS) PRESSURIZATION SYSTEM OF SPACE-CRAFT ENGINE PLANT | 1997 |
|
RU2132477C1 |
| METHOD OF PREPARATION OF HYDROCARBON FUEL FOR GAS- TURBINE ENGINE | 2002 |
|
RU2204728C1 |
| AIRCRAFT SYSTEM FOR REFUELLING RECEIVER AIRCRAFT | 1997 |
|
RU2140381C1 |
