Continuous real time exhaust gas temperature margin control

A method and system for maintaining a limiting gas temperature in a gas turbine engine working fluid flowpath (7) by monitoring the gas temperature and adjusting one or more parameters when the gas temperature exceeds a predetermined or a calculated temperature limit during engine operation. The par...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
1. Verfasser:	VENKATARAMANI KATTALAICHERI SR,LEE CHING-PANG,COOKER PAUL,ORLANDO ROBERT JOSEPH
Format:	Patent
Sprache:	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 JET-PROPULSION 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:	A method and system for maintaining a limiting gas temperature in a gas turbine engine working fluid flowpath (7) by monitoring the gas temperature and adjusting one or more parameters when the gas temperature exceeds a predetermined or a calculated temperature limit during engine operation. The parameters include one or more of a group of engine parameters including high and low pressure turbine nozzle flow areas (42, 52), fan and core flow areas (62, 72), and a rotor speed (N). The one or more parameters are adjusted to lower the gas temperature to below the temperature limit during engine operation. The limiting gas temperature may be a turbine exhaust gas temperature such as a high pressure turbine exhaust gas temperature. The turbine nozzle flow areas may be adjusted with variable nozzle vanes and the fan and core exhaust nozzle flow areas with a translatable fan nozzle cowling and a translatable core nozzle plug, respectively.