GAS TURBINE ENGINE INLET TEMPERATURE SENSOR CONFIGURATION AND CORRESPONDING METHOD

A gas turbine engine (20) includes a compressor (24), a combustor (56) fluidly connected to the compressor (24) via a primary flowpath (C), a turbine (28) fluidly connected to the combustor (56) via the primary flowpath (C), an engine controller (160) communicatively coupled to at least one sensor (...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
1. Verfasser:	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 GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MEASURING MEASURING QUANTITY OF HEAT MEASURING TEMPERATURE MECHANICAL ENGINEERING PHYSICS TESTING THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A gas turbine engine (20) includes a compressor (24), a combustor (56) fluidly connected to the compressor (24) via a primary flowpath (C), a turbine (28) fluidly connected to the combustor (56) via the primary flowpath (C), an engine controller (160) communicatively coupled to at least one sensor (70) in the gas turbine engine (20), the controller (160) including a non-transitory memory and a processor, and the at least one sensor (70) including an inlet temperature and/or pressure sensor, wherein the sensor (70) is disposed aft of a fan (130).