FUEL OIL AXIAL STAGE COMBUSTION FOR IMPROVED TURBINE COMBUSTOR PERFORMANCE

A turbine engine has two combustion zones so as to operate in conditions where water scarcity is an issue. The secondary combustion zone is located downstream of the primary combustion zone. Fuel can be fed into an air scoop having air from a shell surrounding the primary and secondary combustion zo...

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Bibliographische Detailangaben
Hauptverfasser:	MIDUTURI, Krishna C, LASTER, Walter Ray, RAMIER, Stephen A
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A turbine engine has two combustion zones so as to operate in conditions where water scarcity is an issue. The secondary combustion zone is located downstream of the primary combustion zone. Fuel can be fed into an air scoop having air from a shell surrounding the primary and secondary combustion zone. The feeding of the fuel through the air scoop allows atomization of the fuel. The mixture can then enter the secondary combustion zone and mix with the products from the first combustion zone.