MODIFIED START SEQUENCE OF A GAS TURBINE ENGINE

A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor 120, a discrete starter valve 116A switchable between an on-state and an off-state, and a controller 102 operable to perform a starting sequence for the gas turbine engine. The starti...

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Bibliographische Detailangaben
Hauptverfasser:	PINEDO, Victor M, HOOVER, Philip D, SOLOMONIDES, Jason B, GLAHN, Jorn A, TEICHOLZ, Matthew D, GREENE, William H, WHITE, Kenneth J, FEULNER, Matthew R, VIRTUE, John P, SUTLIFF, Jeffrey W
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor 120, a discrete starter valve 116A switchable between an on-state and an off-state, and a controller 102 operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device 110 coupled to the discrete starter valve 116A to achieve a partially open position of the discrete starter valve 116A to control a flow from a starter air supply to the pneumatic starter motor 120 to drive rotation of a starting spool 32 of the gas turbine engine below an engine idle speed.