System and method for air extraction from gas turbine engines

The invention relates to a system and a method for air extraction from gas turbine engines. The disclosed embodiments relate to a system (10) and method (120) that allows air to be extracted from a plurality of gas turbine engines (22, 24, 26) and fed to a downstream process (18), even in situations...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	ALEXANDER MICHAEL JOSEPH, NENMENI VIJAY ANAND RAGHAVENDRAN, PLUMMER PAUL WILLIAM, JANSSEN TIMOTHY LEE
Format:	Patent
Sprache:	chi ; eng
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 INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 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:	The invention relates to a system and a method for air extraction from gas turbine engines. The disclosed embodiments relate to a system (10) and method (120) that allows air to be extracted from a plurality of gas turbine engines (22, 24, 26) and fed to a downstream process (18), even in situations in which one or more of the gas turbine engines (22, 24, 26) are operating in a part load condition. For example, in an embodiment, a method (120) includes monitoring signals representative of a header pressure of a header (14), or a pressure of extraction air flow from one or more gas turbine engines (22, 24, 26) to the header (14), or both, and maintaining substantially continuous flows of extraction air from the gas turbine engines (22, 24, 26) to the header (14). The substantially continuous flows are maintained when the gas turbine engines (22, 24, 26) are under symmetric and asymmetric load conditions.