求教CFM56-5B燃油流量传感器工作原理，还在读书做设计要用

snoopy28

求教CFM56-5B燃油流量传感器工作原理，还有常见故障之类的。还在读书做设计要用嗒，能详细点最好谢谢啦

snoopy28

着急呀

archie

The fuel system enables delivery of a fuel flow corresponding to the power required and compatible with engine limits.
The system consists of:
-     the two stage fuel pump with low pressure and high pressure elements,  
-     the Fuel Metering Unit (FMU),  
-     the engine Fuel Cooled Oil Cooler (FCOC),  
-     the Integrated Drive Generator (IDG) Fuel Cooled Oil Cooler (FCOC),  
-     the fuel filter,  
-     the fuel distribution valve,  
-     the fuel flow meter,  
    20 fuel nozzles,  
the fuel diverter and return (to tank) valve.  
3. Distribution  
The fuel supplied from aircraft tanks flows through a centrifugal pump Low Pressure (LP) stage then through the FCOC and then through a filter and a gear pump High Pressure (HP) stage.
The fuel from the HP pump is delivered to the FMU which controls the fuel flow supplied to the fuel nozzles (through the fuel flow-meter and the fuel distribution valve).
The FMU also provides hydraulic pressure to all hydraulic system external actuators. These include the booster stage bleed valve actuators, stator vane actuator, Air Cooler Oil Cooler (ACOC) air modulating valve, High Pressure Turbine Active Clearance Control (HPTACC) and Low Pressure Turbine Active Clearance Control (LPTACC) valve. Low pressure return fuel from the actuators is routed back into the fuel diverter and return valve.
The fuel diverter and return valve enables the selection of one of the four basic configurations between which the flow paths of the fuel in the engine are varied to maintain the IDG oil, engine oil and fuel temperatures within specified limits.
The transfer between configurations is determined by a software logic contained in the Electronic Engine Control (EEC).
4. Controlling  

The Full Authority Digital Electronic Control (FADEC) system provides full range control of the engine to achieve steady state and transient performance when operated in combination with aircraft subsystems.
The FADEC is a dual channel EEC with crosstalk and failure detection capability.
In case of failure detection, the FADEC switches from one channel to the other.
The FADEC system operates in conjunction with the applicable aircraft systems to perform the following:
-     Control of fuel flow, stator vanes and bleeds to automatically maintain forward and reverse thrust settings and to provide satisfactory transient response.  
-     Protect the powerplant from exceeding limits for N1, N2, maximum allowable thrust, and burner pressure.  
-     Control of the High Pressure Turbine (HPT) 10th stage cooling air, and low and high turbine active clearance control systems.  
-     Control of fuel, engine and IDG oil temperature.  
-     Control of the thrust reverser.  
-     Automatic sequencing of the start system components.  
-     Diagnosis and maintenance capability.  

5. Indicating  
The engine fuel system is monitored from:
-     the ECAM display,  
-     the warning and caution lights.  
The indications cover all the main engine parameters through the FADEC.
The warnings and cautions reflect:
-     the engine health and status through the FADEC,  
-     the FADEC health & status,  
-     the fuel filter condition through a dedicated hardwired pressure switch.