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Research On Cooling Technology Of A Trapped Vortex Combustor

Posted on:2013-07-27Degree:MasterType:Thesis
Country:ChinaCandidate:L WangFull Text:PDF
GTID:2232330362470661Subject:Aerospace Propulsion Theory and Engineering
Abstract/Summary:
The cooling structure for a trapped vortex combustor(TVC) test rig was designed in this paper.First, temperature distribution on liner was studied by numerical simulation. And then experimentalstudy of cooling characteristic on TVC was carried out to investigate the impact of the Mach number,inlet temperature and total air ratio. The results of numerical simulation were compared and verifiedto experimental results. Finally, the influence of three different cooling structures on combustionperformance and cooling characteristic was numerical studied.The results show that the hot spot wall appears on the front and after wall of trapped-vortexcavity, after flame-connected board and mixed zone. The places between injections on mixed zonewall are hotter than places right after injections. Part of added cavity air protects after-wall of cavityin short distance. With decreasing the overall air ratio, Mach number and increasing inlet temperature,wall temperature and gradient increases. Outlet temperature distribution is affected by coolingstructures on wall of mixed zone. The research results show that impingement/effusion coolingstructure owns the best cooling characteristic in three cooling structures.
Keywords/Search Tags:aerospace propulsion system, TVC, combustor cooling technology, effusion cooling, impingement/effusion cooling
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