Methods and apparatus for reducing thermal stresses within turbine engines

A fuel injection system for use with a gas turbine engine (10) includes a plurality of thermally compatible fuel nozzles (50). Each fuel nozzle includes a delivery system (60) to deliver a fluid supply to the gas turbine engine and a support system (62) for supporting the delivery system. The delive...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	MANCINI, ALFRED A, SCHILLING, JAN CHRISTOPHER
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING BURNERS COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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