GAS TURBINE THERMAL SOAK-BACK MITIGATION

There is provided a method 200A of operating a gas turbine engine 101 having a spool 121, 122. The method comprises executing 220A, by a controller 190, a shutdown procedure. The shutdown procedure includes: performing 225A an idle rotation operation; determining 222A a parameter associated with a t...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	Wieland, Jonathan, Donnelly, David M, Wall, Derek S
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 ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	There is provided a method 200A of operating a gas turbine engine 101 having a spool 121, 122. The method comprises executing 220A, by a controller 190, a shutdown procedure. The shutdown procedure includes: performing 225A an idle rotation operation; determining 222A a parameter associated with a thermal condition of the gas turbine engine 101 while the idle rotation operation is performed; determining 224A, based on the determined parameter, whether the gas turbine engine 101 has met a predetermined criterion corresponding to a thermally stabilised condition; and terminating 229A the idle rotation operation in response to a determination that the gas turbine engine 101 has met the pre-determined criterion.