2451144-A is referenced by 8 patents and cites 4 patents.

A system 200 for actively controlling fuel flow from a fuel pump 202 to a mixer assembly 100 of a gas turbine engine combustor (26 fig 1) has at least one sensor 218 for detecting dynamic pressure in the combustor, a fuel nozzle (68 fig 4) for delivering fuel to the combustor, a controller 204 and an arrangement of valves 184, 186, 188 for controlling fuel flow supplied to the nozzle. The valves are in flow communication with a fuel manifold 174, and the controller activates the valves in accordance with a signal received from the pressure sensor. The mixer assembly has a pilot mixer 102 and a main mixer 104.; The pilot mixer includes an annular pilot housing 108 having a hollow interior, a primary fuel injector 110 mounted in the pilot housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, and a plurality of axial swirlers 112, 114 positioned upstream from the primary fuel injector 110. The use of active control identifies and counteracts the onset of a blow-out condition and improves pressure conditions within the combustor.

Title
Method and apparatus for actively controlling fuel flow to a mixer assembly of a gas turbine engine combustor
Application Number
GB20070014583 20070716
Publication Number
2451144 (A)
Application Date
July 16, 2007
Publication Date
January 21, 2009
Inventor
Mongia Hukam Chand
US
Hsieh Shih Yang
US
Li Shui Chi
US
Hsiao George Chia Chun
US
Mancini Alfred Albert
US
Myers William Joseph Jr
US
Assignee
Gen Electric
US
IPC
F23R 03/34
F02C 09/00
F23R 03/34
F02C 09/28
F02C 09/26
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