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Title: Fuel nozzle for a combustor of a gas turbine engine

A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages.
Authors:
; ;
Publication Date:
OSTI Identifier:
1243327
Report Number(s):
9,291,103
13/705,443
DOE Contract Number:
FC26-05NT42643
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Dec 05
Research Org:
GENERAL ELECTRIC COMPANY, Schenectady, NY (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
24 POWER TRANSMISSION AND DISTRIBUTION; 33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING