Gas turbine engine mixing duct and method to start the engine
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United States of America Patent
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Jul 8, 2014
Grant Date -
Apr 26, 2007
app pub date -
Oct 21, 2005
filing date -
Oct 21, 2005
priority date (Note) -
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Abstract
A combustion chamber device having a field static pressure gradient adapted to expel a flame kernel or hot spot from a fuel-air mixing duct. The swirling flow passing through an annular mixing duct is turned from a radial direction to an axial direction before entering the combustion chamber. An ignition source located within the fuel-air mixing duct can then be used to start the combustion process in the gas turbine.
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