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Title: Swirl-counter-swirl microjets for thermoacoustic instability suppression

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.
Inventors:
; ; ;
Issue Date:
OSTI Identifier:
1130303
Assignee:
Massachusetts Institute of Technology (Cambridge, MA) NETL
Patent Number(s):
8,708,696
Application Number:
12/941,177
Contract Number:
FC26-02NT41431
Resource Relation:
Patent File Date: 2010 Nov 08
Research Org:
Massachusetts Institute of Technology, Cambridge, MA (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Works referenced in this record:

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Flow structures in a lean-premixed swirl-stabilized combustor with microjet air injection
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