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AssigneeAlliedSignal Inc.
InventorsJohn E. Dudd, Jr., Dennis G. Demers
Estimating the term…
A turbine engine (49) fuel delivery system of the type including a pneumatic governor has an electronic governor and an engine excess stress avoidance feature which disable the pneumatic governor (70) so long as the engine speed exceeds a prescribed value and an electronic control unit (45) continues to function properly. The system transfers governing responsibility to the electronic control unit (45) which controls a torque motor and solenoid valve fuel diversion line (22). The system monitors an engine (49) operating parameter such as gas generator speed (37), power turbine speed, engine output torque, or engine temperature and further diminishes fuel flow to the engine (49) when the monitored parameter exceeds a threshold value. The system resumes normal speed governoring flow when that parameter returns to an acceptable level The system also senses rotor blade pitch to reduce rotor droop and increases fuel flow to the engine (49) when the pitch (44) increases, and decreasing the fuel flow to the engine (49) when the rotor blade pitch (44) decreases.
An aircraft having an engine and an engine fuel supply system including a fuel pump, a fuel control valve for controlling the flow of fuel from the pump to the engine and a pneumatic engine speed governor, the improvement comprising:
A fuel delivery system for use with an aircraft turbine engine of the type having a gas generator, a generator driven turbine and a pneumatic engine speed governor, comprising a fuel control valve for supplying metered fuel flow to an engine, a fuel pump for supplying fuel from a fuel source to the fuel control valve, a first fuel bypass for diverting fuel exiting the fuel control valve away from the engine and back to the fuel pump to maintain a relatively constant pressure differential across the fuel control valve, a second fuel bypass operable independently from the first fuel bypass and for diverting fuel exiting the control valve away from the engine and back to the fuel pump to maintain at least one of turbine speed, gas generator speed, engine output torque and engine temperature below respective threshold level, and means for disabling the pneumatic engine speed governor and selectively enabling the second fuel bypass when the engine reaches normal idle speed whereby the second fuel bypass may assume the engine speed governing function.
Dependencies are inferred from the claim text.