Gas turbine engine rotor lock prevention system and method

Details Gas turbine engine rotor lock prevention system and method Gas turbine engine rotor lock prevention system and method

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 21/14 (2006.01) B64D 45/00 (2006.01) F01D 21/04 (2006.01) F02C 7/262 (2006.01)

Patent

CA 2662500

A system and method of at least reducing the likelihood of a rotor lock in an aircraft gas turbine engine is provided. A determination is made that each propulsion gas turbine engine on an aircraft has experienced a flameout. The rotational speed of each propulsion gas turbine engine is compared to a predetermined threshold rotational speed and, if the rotational speed of each propulsion gas turbine engine is below the predetermined threshold rotational speed, a warning is supplied to a flight crew.

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