| 摘要 |
Bleed air flow from each engine of a multi-engine gas turbine powered aircraft is determined by using venturi flow probe sensors (50,100) which each include a venturi (52,102). The pressure differential associated with the pressure within the throat of the venturis (52,102) and the pressure immediately upstream of the venturi is partially indicative of the bleed air flow associated with the respective engine. The appropriate sensed pressure and temperature values are provided to a controller (18) which calculates the bleed air flow from each engine. The controller (18) also calculates a trim signal (224) which is used to partially control the position of pressure regulating valves (14,64) in order to substantially equalize the flow of bleed air from each of the gas turbine engines. <IMAGE> |
