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...

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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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Beschreibung
Zusammenfassung:	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 delivery system is disposed within the support system and is subjected to lower operating temperatures than the support system. The delivery system is fabricated from a material having a coefficient of expansion approximately twice a coefficient of expansion for the material used in fabricating the support system.