Low nox gas turbine combustor liner with elliptical apertures for air swirling
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United States of America Patent
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Mar 1, 1994
Grant Date -
N/A
app pub date -
Nov 12, 1992
filing date -
Nov 12, 1992
priority date (Note) -
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Abstract
A gas turbine combustor comprises a plurality of circumferentially spaced can type combustion liners disposed between inner and outer casings of the gas turbine engine. Each combustion liner has an auxiliary set of circumferentially spaced air slots behind a set of circumferentially spaced primary air holes that introduce compressor discharge air to cool hot spots in the primary combustion zone. The air slots are set at an angle so that the compressor discharge air is admitted into the combustion liner in such a way as to induce a swirling motion in the primary combustion zone. The combustion liner also has a set of circumferentially spaced dilution air holes that are sized and located upstream far enough to maintain an acceptable exit temperature profile and acceptable low level carbon monoxide and unburned hydrocarbons emissions.
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