Patent ID: 6339923
Filing Date: 2002-01-22
Classification: F23R

Abstract:
A fuel air mixer for a gas turbine engine combustor having a longitudinal axis therethrough, comprising:(a) a fuel injection assembly having a first end, a second end, a fuel passage extending therethrough, and a flange portion having a plurality of spaced openings formed therein which extends from said first end, said fuel injection assembly further comprising: (1) an elongated fuel stem extending from said first end to said second end, said fuel stem including said fuel passage from said first end to said second end; (2) a fuel inlet in flow communication with said fuel passage in said fuel stem adjacent said first end thereof; and (3) a plurality of fuel injectors in flow communication with said fuel passage in said fuel stem adjacent said second end thereof; wherein fuel entering said fuel air mixture at said fuel inlet is provided through said fuel stem passage and injected into a combustion zone through said fuel injectors; and(b) a mixture assembly having a first end, a second end, a cavity formed in a central portion thereof, and a flange portion having a plurality of spaced openings formed therein which extends from said first end; wherein said mixer assembly is configured to receive said fuel injection assembly in said cavity so that said fuel injection assembly and said mixture assembly are able to be connected to a casing of said combustor by means of said flange portions.