Fuel system for a turbo machine
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United States of America Patent
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Dec 1, 1992
Grant Date -
N/A
app pub date -
Apr 30, 1991
filing date -
Apr 30, 1991
priority date (Note) -
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Abstract
Complexity in a fuel injection system for a gas turbine engine including an annular combustor (26) may be reduced by utilizing a plurality of circumferentially spaced fuel injectors (46) within the annular combustion (26). First and second conduit branches (108, 110; 120, 122) in fluid parallel with one another are provided with one of the branches (108; 120) being connected to at least one of the injectors (46-1; 46-1, 46-3, 46-5) and the other of the branches (110; 122) being connected to the remainder of the injectors (46-2 through 46-6, inclusive; 46-2, 46-4, 46-6). A pump (102) interconnects a source of fuel (100) and the branches (108, 110; 120, 122). A normally closed, pressure responsive valve (114) isolates the other branch (110, 122) from the source (100) at low pressures typical of the starting of the turbine engine and is openable at somewhat higher pressures to allow fuel to flow to all of the injectors (46).
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