Radially staged RQL combustor with tangential fuel-air premixers
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United States of America Patent
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Apr 22, 2014
Grant Date -
Feb 21, 2008
app pub date -
Jun 19, 2007
filing date -
Jun 26, 2006
priority date (Note) -
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Abstract
A double annular radially staged combustor for a gas turbine engine having a reduced internal flow transitioning area between an outboard primary combustion zone and al inboard secondary combustion zone. The primary combustion zone is an annular shell form with a radially inboard annular exit. An outboard ring with thru holes and an inboard annular channel yields a quick quench zone. The secondary combustion zone, adjacent to and downstream of the quick quench zone is of an annular shell form, generally radially inboard of the primary combustion zone. In a preferred embodiment the secondary combustion zone exiting hot gases flows into a dilution zone prior to exiting the combustor.
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