Swirl-counter-swirl microjets for thermoacoustic instability suppression
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United States of America Patent
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Apr 29, 2014
Grant Date -
Jul 7, 2011
app pub date -
Nov 8, 2010
filing date -
Jan 5, 2010
priority date (Note) -
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Abstract
Combustor. The combustor includes an axially symmetric tube along with means for introducing fuel and air into the tube. A swirler is disposed within the tube to impart rotation in a first direction to the air/fuel mixture. A plurality of holes downstream of the swirler are disposed around the tube and offset at an angle relative to an inward normal to the tube wall. Air is injected through the offset holes to impart rotation to the air/fuel mixture in a second direction opposite to the first direction. A combustion chamber having a diameter larger than that of the tube receives and burns the air/fuel mixture from the tube.
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