Development of a Hybrid/Dual Swirl Jet Combustor for a Micro-Gas Turbine (Part II: Numerical Analysis on Isothermal Flow Structure)
마이크로 가스터빈을 위한 하이브리드/이중 선회제트 연소기의 개발 (Part II: 비반응 유동구조에 관한 수치해석)
- Published : 2012.04.13
Abstract
The isothermal flow structure and mixing characteristics of a hybrid/dual swirl jet combustor for micro-gas turbine were numerically investigated. Location of pilot nozzle, angle and direction of swirl vane were varied as main parameters with constant fuel flow rates for each nozzle. As a result, the variation in location of pilot nozzle resulted in significant change in turbulent flow field near burner exit, in particular, center toroidal recirculation zone (CTRZ) as well as turbulent intensity, and thus flame stability and emission characteristics might be significantly changed. The swirl angle of
Keywords
- Hybrid/dual swirl jet combustor;
- Lean-premixed combustor;
- Low NOx combustor;
- Micro-gas turbine;
- Isothermal flow structure