Impact of fuel injection modes on combustion and emissions of coaxial staged combustor
-
摘要:
针对贫预混短距离柴油快速雾化蒸发困难和油气掺混均匀性差的问题，采用试验与数值模拟方法结合的方式，分析了双流体雾化喷嘴在垂直和水平两种喷射模式下，以及不同燃油分配比例条件下，柴油同轴分级燃烧室的性能变化情况。研究结果表明：在模化设计工况下，燃油水平喷射方案油气分布均匀性优于垂直喷射方案，垂直喷射方案近壁面高温区增加导致排放和出口温度恶化。在模化0.35～1.0工况下，主燃级水平喷射值班级燃油比例增加，NOx先增加后降低，CO和出口温度分布系数总体呈增大趋势。经过宽工况条件下的试验研究，给出了不同工况下的最佳燃油分配比例。
Abstract:In response to the challenges of difficult rapid evaporation and poor uniformity of the fuel-air mixture in lean premixed gas turbine combustion, an experimental and numerical simulation method was employed to analyze the impact of dual-fluid atomization nozzles under vertical and horizontal injection modes, by considering different fuel distribution ratios on the performance of a coaxial staged combustor. The results showed that under the simulated conditions, the horizontal fuel injection mode exhibited better uniformity of fuel distribution compared with the vertical injection scheme. Under vertical injection conditions, an increase in near-wall high-temperature areas led to elevated emissions and a deteriorated outlet temperature distribution. Under the 0.35—1.0 conditions, as the main fuel ratio in the primary stage increased with horizontal injection, NOx initially increased and then decreased, while CO and outlet temperature distribution factor showed an overall increasing trend. Through experimental studies conducted under wide operating conditions, optimal fuel distribution ratios under different conditions were determined.
-
图 3 单点贫油直喷燃烧室不同横截面速度分布
Figure 3. Velocity distribution at different cross-sections of the single-point lean direct injection combustor
图 4 燃烧室模化设计工况不同燃油喷射模式下当量比分布
Figure 4. Equivalence ratio distribution under different fuel injection modes for the model combustor design conditions
图 5 燃烧室模化设计工况不同燃油喷射模式下温度分布
Figure 5. Temperature distribution under different fuel injection modes for the model combustor design conditions
图 6 燃烧室模化设计工况不同燃油喷射模式下OH和NO质量分数分布
Figure 6. OH and NO mass fraction distribution under different fuel injection modes for the model combustor design conditions
图 7 燃烧室模化设计工况不同燃油喷射模式下出口温度分布
Figure 7. Exit temperature distribution under different fuel injection modes for the model combustor design conditions
图 8 燃烧室模化设计工况不同值班级燃油分配比例时试验结果
Figure 8. Experimental results under different fuel distribution ratios in the pilot stage for model combustor design conditions
图 9 燃烧室模化0.8工况不同值班级燃油分配比例时试验结果
Figure 9. Experimental results under different fuel distribution ratios in the pilot stage for the model combustor at 0.8 conditions
图 10 燃烧室模化0.7工况不同值班级燃油分配比例时试验结果
Figure 10. Experimental results under different fuel distribution ratios in the pilot stage for the model combustor at 0.7 conditions
图 11 燃烧室模化0.6工况不同值班级燃油分配比例时试验结果
Figure 11. Experimental results under different fuel distribution ratios in the pilot stage for the model combustor at 0.6 conditions
图 12 燃烧室模化0.5工况不同值班级燃油分配比例时试验结果
Figure 12. Experimental results under different fuel distribution ratios in the pilot stage for the model combustor at 0.5 conditions
图 13 燃烧室模化0.35工况不同值班级燃油分配比例时试验结果
Figure 13. Experimental results under different fuel distribution ratios in the pilot stage for the model combustor at 0.35 conditions
表 1 模化试验燃烧室运行工况参数
Table 1. Parameters in operating conditions of the model test combustor
工况 空气质量流量/
（kg/s）空气
温度/K燃油质量流量/
（kg/s）0.35 0.676 659 0.0116 0.5 0.652 693 0.0125 0.6 0.642 710 0.0131 0.7 0.63 727 0.0135 0.8 0.62 742 0.014 1.0 0.601 770 0.0148 
下载: 导出CSV
表 2 燃烧室模化设计工况性能与污染物排放
Table 2. Performance and emissions of the model combustor design conditions
喷射方式 压力损失系数/% 燃烧效率/% NOx@15%O2/10−6 CO@15%O2/10−6 OTDF/% 水平喷射 3.63 99.76 32.4 28.2 22.3 垂直喷射 3.64 99.82 58.1 26.2 37.9
下载: 导出CSV
-
[1] 尉曙明, 索建秦. 航空衍生工业燃气轮机双燃料贫燃预混低污染燃烧技术[J]. 航空动力学报, 2015, 30(9): 2049-2057. WEI Shuming, SUO Jianqin. Aero-derivative industrial gas turbine dual fuel lean premixed low emission combustion technology[J]. Journal of Aerospace Power, 2015, 30(9): 2049-2057. (in Chinese doi: 10.13224/j.cnki.jasp.2015.09.001WEI Shuming, SUO Jianqin. Aero-derivative industrial gas turbine dual fuel lean premixed low emission combustion technology[J]. Journal of Aerospace Power, 2015, 30(9): 2049-2057. (in Chinese) doi: 10.13224/j.cnki.jasp.2015.09.001 [2] 李苏辉, 张归华, 吴玉新. 面向未来燃气轮机的先进燃烧技术综述[J]. 清华大学学报(自然科学版), 2021, 61(12): 1423-1437. LI Suhui, ZHANG Guihua, WU Yuxin. Advanced combustion technologies for future gas turbines[J]. Journal of Tsinghua University (Science and Technology), 2021, 61(12): 1423-1437. (in Chinese doi: 10.16511/j.cnki.qhdxxb.2022.25.001LI Suhui, ZHANG Guihua, WU Yuxin. Advanced combustion technologies for future gas turbines[J]. Journal of Tsinghua University (Science and Technology), 2021, 61(12): 1423-1437. (in Chinese) doi: 10.16511/j.cnki.qhdxxb.2022.25.001 [3] LEFEBVRE A H, BALLAL D R. Gas turbine combustion[M]. Boca Raton, US: Taylor & Francis, 2010. [4] CHEN Z X, LANGELLA I, SWAMINATHAN N, et al. Large eddy simulation of a dual swirl gas turbine combustor: flame/flow structures and stabilisation under thermoacoustically stable and unstable conditions[J]. Combustion and Flame, 2019, 203: 279-300. doi: 10.1016/j.combustflame.2019.02.013 [5] DHANUKA S K, TEMME J E, DRISCOLL J F. Unsteady aspects of lean premixed prevaporized gas turbine combustors: flame-flame interactions[J]. Journal of Propulsion and Power, 2011, 27(3): 631-641. doi: 10.2514/1.B34001 [6] 刘易安, 郭志辉, 张漫. 中心分级燃烧室雾化特性试验研究[J]. 推进技术, 2019, 40(8): 1824-1831. LIU Yian, GUO Zhihui, ZHANG Man. Experimental investigation on spray characteristic of internally-staged combustor[J]. Journal of Propulsion Technology, 2019, 40(8): 1824-1831. (in Chinese doi: 10.13675/j.cnki.tjjs.180490LIU Yian, GUO Zhihui, ZHANG Man. Experimental investigation on spray characteristic of internally-staged combustor[J]. Journal of Propulsion Technology, 2019, 40(8): 1824-1831. (in Chinese) doi: 10.13675/j.cnki.tjjs.180490 [7] 刘富强, 穆勇, 刘存喜, 等. 燃油分级对中心分级燃烧室NOx排放的影响[J]. 燃烧科学与技术, 2013, 19(3): 254-260. LIU Fuqiang, MU Yong, LIU Cunxi, et al. Influence of fuel stage proportion on NOx emission from central stage combustor[J]. Journal of Combustion Science and Technology, 2013, 19(3): 254-260. (in ChineseLIU Fuqiang, MU Yong, LIU Cunxi, et al. Influence of fuel stage proportion on NOx emission from central stage combustor[J]. Journal of Combustion Science and Technology, 2013, 19(3): 254-260. (in Chinese) [8] 马存祥, 孙露, 马鑫, 等. 贫油预混预蒸发燃烧室燃烧不稳定性试验研究[J]. 推进技术, 2019, 40(3): 602-607. MA Cunxiang, SUN Lu, MA Xin, et al. Experimental study on combustion instability of lean premixed pre-vaporized combustor[J]. Journal of Propulsion Technology, 2019, 40(3): 602-607. (in Chinese doi: 10.13675/j.cnki.tjjs.180126MA Cunxiang, SUN Lu, MA Xin, et al. Experimental study on combustion instability of lean premixed pre-vaporized combustor[J]. Journal of Propulsion Technology, 2019, 40(3): 602-607. (in Chinese) doi: 10.13675/j.cnki.tjjs.180126 [9] HICKS Y R, CAPIL T, AADERSON R. Flame tube testing of a gea taps injector: effects of fuel staging on combustor fuel spray patterns, flow structure, and speciation[R]. AIAA-2018-4476, 2018. [10] 程明, 尚守堂, 刘殿春, 等. 燃油分级比例对TAPS燃烧室性能的影响[J]. 航空发动机, 2012, 38(4): 6-10. CHENG Ming, SHANG Shoutang, LIU Dianchun, et al. Influence of fuel-staging ratio on TAPS combustor performance[J]. Aeroengine, 2012, 38(4): 6-10. (in ChineseCHENG Ming, SHANG Shoutang, LIU Dianchun, et al. Influence of fuel-staging ratio on TAPS combustor performance[J]. Aeroengine, 2012, 38(4): 6-10. (in Chinese) [11] HOFFMANN S, JUDITH H, HOLM C G. Further development of the siemens LPP hybrid burner[R]. Stockholm, Sweden: ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition, 1998. [12] 邓远灏, 朱嘉伟, 颜应文, 等. LPP低污染燃烧室冷态流场与油雾特性[J]. 南京航空航天大学学报, 2013, 45(2): 162-169. DENG Yuanhao, ZHU Jiawei, YAN Yingwen, et al. Cold flow field and fuel spray characteristic of LPP low emission combustor[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2013, 45(2): 162-169. (in Chinese doi: 10.3969/j.issn.1005-2615.2013.02.002DENG Yuanhao, ZHU Jiawei, YAN Yingwen, et al. Cold flow field and fuel spray characteristic of LPP low emission combustor[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2013, 45(2): 162-169. (in Chinese) doi: 10.3969/j.issn.1005-2615.2013.02.002 [13] 王智勇, 王波, 韩啸, 等. TeLESSⅡ低排放燃烧室预燃级设计对排放的影响[J]. 航空动力学报, 2017, 32(7): 1561-1568. WANG Zhiyong, WANG Bo, HAN Xiao, et al. Influence of pre-combustion stage design of TeLESSⅡ low emission combustion chamber on emissions[J]. Journal of Aerospace Power, 2017, 32(7): 1561-1568. (in Chinese doi: 10.13224/j.cnki.jasp.2017.07.004WANG Zhiyong, WANG Bo, HAN Xiao, et al. Influence of pre-combustion stage design of TeLESSⅡ low emission combustion chamber on emissions[J]. Journal of Aerospace Power, 2017, 32(7): 1561-1568. (in Chinese) doi: 10.13224/j.cnki.jasp.2017.07.004 [14] FOUST M, THOMSEN D, STICKLES R, et al. Development of the GE aviation low emissions TAPS combustor for next generation aircraft engines[R]. AIAA-2012-0936, 2012. [15] FUJIWARA H, MATSUURA K, SHIMODAIRA K, et al. Suppression of NOx emission of a lean staged combustor for an aircraft engine[R]. Vancouver, Canada: ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, 2011. [16] 陆景贺, 刘潇, 刘恩惠, 等. 船用低排放塔式分级燃烧室主燃级喷嘴结构优化研究[J]. 推进技术, 2022, 43(9): 210352. LU Jinghe, LIU Xiao, LIU Enhui, et al. Optimization research on main stage atomizer structure of marine low emission tower-type coaxial-staged combustor[J]. Journal of Propulsion Technology, 2022, 43(9): 250. (in Chinese doi: 10.13675/j.cnki.tjjs.210352LU Jinghe, LIU Xiao, LIU Enhui, et al. Optimization research on main stage atomizer structure of marine low emission tower-type coaxial-staged combustor[J]. Journal of Propulsion Technology, 2022, 43(9): 250. (in Chinese) doi: 10.13675/j.cnki.tjjs.210352 [17] TAN Z P, LUBARSKY E, BIBIK O, et al. Effect of air-assist on liquid jet penetration and dispersion in a cross-flow of hot, high-pressure air[R]. ASME GT2015-42239, 2015. [18] TAN Z P, LUBARSKY E, BIBIK O, et al. The effects of air-assist upon liquid fuel jet penetration and dispersion in a cross-flow of preheated air[J]. Atomization and Sprays, 2016, 26(11): 1177-1196. doi: 10.1615/AtomizSpr.2015013586 [19] TAN Z P. The physics of twin-fluid jet-in-crossflow at atmospheric and jet-engine operating conditions[J]. Physics of Fluids, 2019, 31(4): 045106. doi: 10.1063/1.5090110 [20] LUO Zhaoyu, SOM S, SARATHY S M, et al. Development and validation of an n-dodecane skeletal mechanism for spray combustion applications[J]. Combustion Theory and Modelling, 2014, 18(2): 187-203. doi: 10.1080/13647830.2013.872807 [21] CAI J, JENG S M, TACINA R. The structure of a swirl-stabilized reacting spray issued from an axial swirler[R]. AIAA-2005-1424, 2005. -
点击查看大图
计量
- 文章访问数: 543
- HTML浏览量: 306
- PDF量: 49
- 被引次数: 0