Device and process for regulating the power of the engines of a rotary wing multi-engine aircraft. The regulating device (1) comprises, in addition to main regulating systems (2, 6) associated with the engines (M1, M2) of the aircraft, auxiliary regulating systems (12, 13) associated with said engines (M1, M2) and means (10, 11) for determining the speeds of rotation of the engines (M1, M2). Each auxiliary regulating system (12, 13) is capable of automatically adjusting the flow rate of fuel in such a way as to slave the speed of rotation of the associated engine, when its main regulating system has failed, to the speed of rotation of the other engine of the aircraft.

The invention provides methods, systems, and products for communicating between engine computers without the participation of a flight deck computer. The invention allows the engine computers to coordinate activities for real-time control of the engines for improved efficiency using an existing ARINC 429 communications bus. The invention facilitates cross-engine communications over the same ARINC 429 communications bus used for communicating with the Flight Deck Computer, without installation of a second, dedicated communications bus for cross-engine communications. The invention thus provides a cost effective way to allow the engines to coordinate activities without expensive installation and recertification of airframe modifications.

Control logic, and a method implemented by the control logic, compensates for mismatched inter turbine temperatures between two gas turbine engines and displays a biased inter turbine temperature (ITT) reading to the pilot without jeopardizing the need to be properly informed of the health of all engines and the relationship engine temperature compared to the maximum allowed temperature. A temperature compensation value is added to the lower inter turbine temperature to thereby increase the ITT to a value that is substantially equal to the higher ITT value. As a result, any potential nuisance or distraction that the flight crew may experience from displaying the mismatch is eliminated.

The present invention is addressed to an exciter circuit used as part of an engine ignition system which is controlled by a full authority digital engine control or FADEC. Two channels of the FADEC system are connected to two channels on the exciter system in a cross talk arrangement. This permits any one channel on the FADEC to control both channels on the exciter for redundancy purposes. The establishment of a FADEC control of an exciter system also permits selective use of the exciters and reduces wear on the exciter circuitry and ignition system components.

A system for controlling output torque characteristics of an internal combustion engine includes a control computer operable to control the output power/torque of the engine that is coupled to a transmission through a torque converter. The system is operable to determine an engine speed range of interest and limit engine output power/torque to a predefined maximum value if the current engine speed is within the engine speed range of interest when the torque converter is operating in torque converter mode (i.e., not in lockup mode). The predefined maximum value of engine output power/torque is preferably a maximum horsepower value that may be a constant value or a function of engine speed within the engine speed range of interest. Alternatively, the predefined maximum value of engine output power/torque is a dynamic function of a torque ratio of the torque converter and a predefined turbine torque limit.