United Technologies Corporation

Robert W Rice

David H Sweet

Nicholas D Lappos

James J Howlett

Mark A Johnston

Charles W Evans

Frederick J Ebert

Gregory P Wright

An engine failure monitor 50 for use with a multi-engine aircraft having at least two engines detects conditions indicative of a partial (700) or total (400) engine failure, including turbine shaft failures (600). In response to an engine failure, suitable inputs (134, 138, 712) are provided to an electronic engine control for operating the remaining engine. Additionally, indications indicative of the engine failure (132, 710) are provided to the cockpit.

Engine failure monitor for a multi-engine aircraft having partial engine

A helicopter engine speed reference (66) is increased (117,118) in response to heavy rotor loading (102) in excess of a threshold at the current descent rate (FIG. 4 ). The reference speed is faded up (117,118) at a rapid rate to 107% of rated speed (119). After a fixed time interval (129), reduce rotor loading (122), reduced pitch angle below a threshold magnitude (121) and reduced roll angle below a threshold magnitude (120) will cause the reference speed to be faded down slowly (146,147) to rated speed (148). Automatic increase in engine reference speed is overridden to 107% of rated speed (203) when a battle switch is activated (201) and weapons are ready (202). Increases in engine reference speed are prohibited (207) when the helicopter is operating in quiet mode (206) or the helicopter is resting on its wheels (208).

Helicopter engine speed enhancement during heavy rotor load and rapid

Primary logic (116-128) for engine failure detection in a multi-engine aircraft is based on thresholds for engine torque (Q), gas generator speed (NG), power turbine inner stage temperature (T5), power turbine speed (NF), throttle setting (PLA), and throttle manipulation (PLADOT).

Detection of engine failure in a multi-engine aircraft

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Sandy Hook, CT, United States of America

Robert W Rice