Gas turbine igniter system

F - Mech Eng,Light,Heat,Weapons – 02 – C

Patent

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341/17, 317/5

F02C 9/00 (2006.01)

Patent

CA 1088181

ABSTRACT OF THE DISCLOSURE High energy excitation is automatically provided to the combustor during periods of engine start and engine reignition by way of an alternator driven directly by the engine and connectable to the igniter through an exciter at predetermined periods by a logic control on the engine. Provision is made to automatically turn off the igniter when the engine reaches a predetermined speed, and to automatically turn it on again when the engine deceleration reaches a predetermined rate as would occur when engine flame-out occurs. A separate and independent low-energy ignition system which derives its power from the aircraft is provided so that the operator can maintain continuous low-energy ignition at his discretion.

244918

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