Sikorsky Aircraft Corporation

David H Sweet

Stephen Hilary Silder

Robert J Andrejczyk

A method of adaptive engine acceleration for accessory loads includes receiving an accessory load indicator corresponding to an accessory load of an engine. The accessory load indicator is compared to an adjustment threshold. An acceleration rate of the engine is increased based on determining that the accessory load indicator is below the adjustment threshold. The acceleration rate of the engine is decreased based on determining that the accessory load indicator is above the adjustment threshold.

Adaptive engine acceleration for accessory loads

A gas turbine engine control system according to an exemplary aspect of the present disclosure includes, among other things, an automatic control operable to control a gas turbine engine. The gas turbine engine control system further comprises a module operable to fail-fix the gas turbine engine to one of a multiple of pre-determined modes in response to failure of the automatic control. The exemplary gas turbine engine control system may further comprise a fuel flow meter to sense a fuel flow to the engine, a fuel control to control the fuel flow to the engine, and the module in electrical communication with the fuel flow meter to fix the fuel control in response to one of the multiple of pre-determined modes.

Multi-mode adaptive fail-fixed system for FADEC controlled gas turbine engines

A method of aircraft engine thermal threat mitigation includes detecting an airflow thermal profile at a location on the aircraft forward of an aircraft engine inlet and transmitting the thermal profile to an aircraft control system. The thermal profile is compared to a catalog of thermal threat profiles at the aircraft control system and a determination is made if a thermal threat is present based on the comparison. A thermal threat mitigation measure is initiated to reduce an effect of the thermal threat on aircraft engine performance.

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Jupiter, FL, United States of America

David H Sweet