An integrated experimental and numerical study of meso-scale vortex combustor dynamics

Y. Wang, M. Wu, R. A. Yetter, V. Yang

Research output: Contribution to conferencePaper

4 Scopus citations

Abstract

An integrated experimental and numerical study of meso-scale vortex combustor dynamics has been performed. In the first part, a series of meso-scale vortex stabilized combustors were designed and fabricated. Characterization of the combustion performance was carried out with diagnostic instruments such as FT-IR, gas chromatographer, and thermocouples. Stabilized hydrogen/air and oxygen-enriched methane/air flames can be achieved in a vortex combustor with a volume as small as 10mm3. In the second part, the swirling reacting flow in a vortex combustor was investigated numerically. The model treats the full conservation equations in three dimensions. The numerical algorithm is based on a preconditioned, density-based, finite-volume approach along with a dual-time stepping integration algorithm. Various fundamental mechanisms responsible for flame stabilization were examined systematically. The swirl-induced recirculation zone plays an important role in anchoring flame in a small volume by providing a heat source and a reduced velocity region, which prevents the flame to expand downstream. The energy conversion efficiency strongly depends on the flow evolution in the combustor. The influences of the combustor geometry on the flame dynamics were investigated.

Original languageEnglish (US)
Pages3635-3649
Number of pages15
DOIs
StatePublished - Jan 1 2005
Event43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 10 2005Jan 13 2005

Other

Other43rd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period1/10/051/13/05

All Science Journal Classification (ASJC) codes

  • Engineering(all)

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    Wang, Y., Wu, M., Yetter, R. A., & Yang, V. (2005). An integrated experimental and numerical study of meso-scale vortex combustor dynamics. 3635-3649. Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States. https://doi.org/10.2514/6.2005-941