Swirl-counter-swirl microjets for thermoacoustic instability suppression
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.
- Inventors:
- Issue Date:
- Research Org.:
- Massachusetts Inst. of Technology (MIT), Cambridge, MA (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1130303
- Patent Number(s):
- 8708696
- Application Number:
- 12/941,177
- Assignee:
- Massachusetts Institute of Technology (Cambridge, MA)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23D - BURNERS
- DOE Contract Number:
- FC26-02NT41431
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2010 Nov 08
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Ghoniem, Ahmed F, LaBry, Zachary A, Shanbhogue, Santosh J, and Speth, Raymond L. Swirl-counter-swirl microjets for thermoacoustic instability suppression. United States: N. p., 2014.
Web.
Ghoniem, Ahmed F, LaBry, Zachary A, Shanbhogue, Santosh J, & Speth, Raymond L. Swirl-counter-swirl microjets for thermoacoustic instability suppression. United States.
Ghoniem, Ahmed F, LaBry, Zachary A, Shanbhogue, Santosh J, and Speth, Raymond L. Tue .
"Swirl-counter-swirl microjets for thermoacoustic instability suppression". United States. https://www.osti.gov/servlets/purl/1130303.
@article{osti_1130303,
title = {Swirl-counter-swirl microjets for thermoacoustic instability suppression},
author = {Ghoniem, Ahmed F and LaBry, Zachary A and Shanbhogue, Santosh J and Speth, Raymond L},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2014},
month = {4}
}
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