FIELD: engines and pumps.
SUBSTANCE: system is equipped with a check valve installed at the outlet of the high pressure pump in the fuel supply line before the bypass output connecting and the fuel temperature sensor installed in the fuel supply line after the low pressure pump before the bypass inlet connecting, the high-pressure pump bypass control is designed in the form of a check valve, and the digital regulator is further connected by a communication channel with a fuel temperature sensor.
EFFECT: ensuring the operability of the two-stage fuel feed system while maintaining the permissible fuel metering accuracy when any of the low and high pressure pumps or their electric drives fail.
1 dwg
Title | Year | Author | Number |
---|---|---|---|
GAS TURBINE ENGINE FUEL FEED SYSTEM | 2012 |
|
RU2507407C1 |
FUEL FEED SYSTEM FOR GAS TURBINE ENGINE WITH AUGMENTER | 2012 |
|
RU2507406C1 |
AIRCRAFT GAS TURBINE ENGINE AUTOMATIC CONTROL SYSTEM | 2017 |
|
RU2648479C1 |
GAS TURBINE ENGINE FUEL FEED AND CONTROL SYSTEM | 2001 |
|
RU2194181C1 |
FUEL SUPPLY SYSTEM TO MULTI-COLLECTOR COMBUSTION CHAMBER | 2020 |
|
RU2753207C1 |
ELECTRICALLY DRIVEN PUMP | 2013 |
|
RU2540204C2 |
GAS-TURBINE ENGINE FUEL SUPPLY AND CONTROL SYSTEM | 2002 |
|
RU2228455C2 |
AUTOMATIC CONTROL SYSTEM OF A GAS TURBINE ENGINE | 2020 |
|
RU2751826C1 |
GAS TURBINE ENGINE FUEL FEED SYSTEM | 2008 |
|
RU2368794C1 |
LUBRICATION SYSTEM OF GAS TURBINE ENGINE ROTOR SUPPORT BEARINGS | 2015 |
|
RU2619519C1 |
Authors
Dates
2017-05-16—Published
2015-12-22—Filed