Gas turbine engine combustor

A gas turbine engine combustor (10) is provided and includes an array of fuel nozzles (20), a combustion casing assembly (30) disposed about the array of fuel nozzles (20) and an end cap assembly (40) disposed within the combustion casing assembly (30) to defme with the combustion casing assembly (3...

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Bibliographische Detailangaben
Hauptverfasser:	KIM, KWANWOO, BERRY, JONATHAN DWIGHT, FLAMAND, LUIS M, VANSELOW, JOHN DRAKE, ROHRSSEN, ROBERT JOSEPH, MELTON, PATRICK BENEDICT, BAILEY, DONALD MARK
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 gas turbine engine combustor (10) is provided and includes an array of fuel nozzles (20), a combustion casing assembly (30) disposed about the array of fuel nozzles (20) and an end cap assembly (40) disposed within the combustion casing assembly (30) to defme with the combustion casing assembly (30) an axis-symmetric annulus (50) through which fluid travels into each of the fuel nozzles, at least one of the combustion casing assembly (30) and the end cap assembly (40) being formed with lobed, three-dimensional contouring (60).