| US 7,464,553 B2 | ||
| Air-assisted fuel injector for mixer assembly of a gas turbine engine combustor | ||
| Shih-Yang Hsieh, West Chester, Ohio (US); George Chia-Chun Hsiao, West Chester, Ohio (US); Shui-Chi Li, West Chester, Ohio (US); and Hukam Chand Mongia, West Chester, Ohio (US) | ||
| Assigned to General Electric Company, Schenectady, N.Y. (US) | ||
| Filed on Jul. 25, 2005, as Appl. No. 11/188,470. | ||
| Prior Publication US 2007/0028617 A1, Feb. 08, 2007 | ||
| Int. Cl. F23R 3/14 (2006.01) | ||
| U.S. Cl. 60—748 [60/740] | 20 Claims |
| 1. A mixer assembly for use in a combustion chamber of a gas turbine engine, comprising:
(a) a pilot mixer including an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in said housing
and adapted for dispensing droplets of fuel to said hollow interior of said pilot housing;
(b) a main mixer including:
(1) a main housing surrounding said pilot housing and defining an annular cavity;
(2) a plurality of fuel injection ports for introducing fuel into said annular cavity;
(3) a post member associated with and extending from each said fuel injection port to an inner surface of said annular cavity,
said post member including an inner passage therethrough in flow communication with said fuel injection port;
(4) a passage surrounding each said post member, wherein air is provided therefrom to envelop fuel injected into said annular
cavity; and,
(5) a swirler arrangement including at least one swirler positioned upstream from said fuel injection ports, wherein each
swirler of said arrangement has a plurality of vanes for swirling air traveling through such swirler to mix air and said droplets
of fuel dispensed by said fuel injection ports; and,
(c) a fuel manifold positioned between said pilot mixer and said main mixer, wherein said plurality of fuel injection ports
for introducing fuel into said main mixer cavity are in flow communication with said fuel manifold.
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