| Autor: |
Zhang, Qun1 (AUTHOR) zhangqun@nwpu.edu.cn, Zhang, Peng1 (AUTHOR), Xing, Li2 (AUTHOR), Song, Yaheng1 (AUTHOR), Li, Chengyu1 (AUTHOR), Kou, Rui1 (AUTHOR), Wang, Xin1 (AUTHOR), Hai, Han1 (AUTHOR) |
| Předmět: |
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| Zdroj: |
Energy Sources Part A: Recovery, Utilization & Environmental Effects. 2021, Vol. 43 Issue 2, p184-200. 17p. |
| Abstrakt: |
Lean-premixed combustion technology has been adopted widely for heavy-duty gas turbine application. The multiple-swirl structure might shorten the flame brush length and reduce emissions. However, the inlet flow cannot be set equally for each swirl burner. The inlet guiding ring structure should be carefully adjusted and validated to reach the design goal. This paper introduces a typical geometry of heavy-duty combustor, which is designed with multiple swirler structures. The inlet guiding ring is a semicircle type. The parametric analysis is trying to investigate the axial location of the inlet guiding ring effect on the downstream multiple-swirl flow structure. Computational results show that both the Counter-Swirl and Co-Swirl configurations possess quite well aerodynamics which can support the recirculation establishment and flame stabilization. As the axial distance between the inlet guiding ring and swirl nozzle increases from 16 mm to 37 mm, the width of the recirculation will increase, which intensify the turbulence mixing for the pilot and main stage. Meanwhile, the length of the recirculation also increases, and the turbulence intensity keeps relatively strong. When the gap distance increases from 37 mm to 51 mm, the flow phenomenon would return to the condition like the case with an axial distance equal to 16 mm. Therefore, the condition with the axial gap distance 37 mm is quite critical. Thus, the flow field is quite sensitive to the inlet guiding ring location. [ABSTRACT FROM AUTHOR] |
| Databáze: |
GreenFILE |
| Externí odkaz: |
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