ACTIVE MULTI-EFFECTOR CONTROL OF HIGH PRESSURE TURBINE CLEARANCES

The present invention relates to a method of operating a gas turbine engine (20) for actively controlling the clearances in the high-pressure turbine section, wherein the variable-pitch stator vanes are controlled to reduce rotational speed of the high-pressure shaft in response to an acceleration c...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	LISITANO, Brenda J, HO, Christopher L, DHINGRA, Manuj, KEHOE, Joseph, COUTURE, Patrick D, MEISNER, Richard P, FEULNER, Matthew R
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 JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The present invention relates to a method of operating a gas turbine engine (20) for actively controlling the clearances in the high-pressure turbine section, wherein the variable-pitch stator vanes are controlled to reduce rotational speed of the high-pressure shaft in response to an acceleration command of the gas turbine engine. The variable pitch high pressure compressor vanes (76) are moved toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor (60) thereby reducing a change in a clearance gap (64) between the high pressure turbine rotor and a blade outer air seal (66). By providing a variable-pitch stator vane control in addition to a fluid-based clearance control, the clearance can be controlled more accurately particularly during sharp acceleration of the gas turbine engine.