Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities

(19)

(11)

EP 1 319 896 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	12.05.2004 Bulletin 2004/20

(43)	Date of publication A2:
	18.06.2003 Bulletin 2003/25

(21)	Application number: 02027665.5

(22)	Date of filing: 12.12.2002

(51)	International Patent Classification (IPC)⁷: F23R 3/28

(84)	Designated Contracting States:
	AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SI SK TR
	Designated Extension States:
	AL LT LV MK RO

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Priority:

14.12.2001 US 14415

(71)	Applicant: Mowill, R. Jan
	7550 AV Hengelo (NL)

(72)	Inventor:
	Mowill, R. Jan 7550 AV Hengelo (NL)

(74)	Representative: HOFFMANN - EITLE
	Patent- und Rechtsanwälte Arabellastrasse 4 81925 München 81925 München (DE)

(54)	Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities

(57) Apparatus (1430) for premixing fuel and air to provide a fuel/air mixture includes a mixing tube (1434) configured for receiving fuel and air, a mixing tube axis (1442), and a mixing tube exit (1454) for discharging a fuel/air mixture. The apparatus further includes a mixture valve (1444) associated with the mixing tube exit (1454) and including inner and outer valve members that define an exit flow area (1402). The defined exit flow area includes at least two segmented, substantially opposed area portions with respect to angular position about the mixing tube axis provided by contours in the outer valve member for directing the mixture flow, and at least one of the inner and outer valve members is movable relative to the other of the valve members to selectively vary the defined exit flow area with respect to time. In a gas turbine gas generator or engine application, a separate controllable combustion air valve can be used with a fuel valve to provide controlled fuel/air ratios for the mixture.

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