Combustor for gas turbine engine
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United States of America Patent
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May 1, 2018
Issued Date -
N/A
app pub date -
Mar 12, 2013
filing date -
Mar 12, 2013
priority date (Note) -
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Abstract
A gas turbine engine comprises an annular combustor chamber formed between an inner liner and an outer liner. An annular upstream zone is adapted to receive fuel and air from an annular nozzle. An annular mixing zone is located downstream of the upstream zone. The mixing zone has a reduced radial height relative a downstream combustion zone of the combustion chamber, the mixing zone defined by straight wall sections.
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