带级间燃烧的涡轴发动机性能仿真
Performance simulation of turboshaft engines with interstage turbine burner
-
摘要: 为了分析涡轮级间燃烧技术对常规涡轴发动机性能提升的潜力,针对两种带级间燃烧的涡轴发动机性能方案,分别建立了部件级稳态性能计算模型,并通过仿真对比分析了级间燃烧室不同温升及总压损失条件下发动机的整机性能,结果表明:级间燃烧室总压恢复系数和温升对单位功率和总功率影响较大,当级间燃烧室总压恢复系数为0.95、温升为200K时,保持进口空气流量不变,涡轴发动机单位功率和总功率增加17%,耗油率增加约11%;在高的级间燃烧室温升条件下,适当增加动力涡轮导向器面积,改善涡轮流通能力,有利于进一步提高整机功率,降低动力涡轮前温度;两种方案对比,在涡轮过渡段设置级间燃烧室空间上更好布置,性能上更占优势.Abstract: In order to analysis the turboshaft engine performance increase through interstage turbine burner (ITB),two component-level steady performance simulation models of turboshaft engines with ITB were developed.The performance variations of turboshaft engines with ITB were studied through simulation at different ITB temperature rise and total pressure loss.Results show that:The specific and total shaft power of turboshaft engines with ITB are sensitive to the ITB temperature rise and total pressure recovery coefficients.If the ITB total pressure recovery coefficient is 0.95 and temperature rise is 200K,while keeping the engine inlet air flow constant,the specific and total shaft power of turboshaft engine with ITB will increase 17%,and the specific fuel consumption will increase 11%.When the ITB temperature rise is high,it is necessary to enlarge free turbine nozzle area to improve the flow capability,so as to further increase the total shaft power and lower the free turbine inlet temperature;In general,it is better to set the ITB in turbine transition duct for more sufficient space and more excellent performance improvements.
-
Key words:
- turboshaft engine /
- interstage turbine burner /
- performance simulation /
-
[1] Sirignano W A,Liu F.Performance increases for gas-turbine engines through combustion inside the turbine[J].Journal of Propulsion and Power,1999,15(1):111-118. [2] Liu F,Sirignano W A.Turbojet and turbofan engine performance increases through turbine burners .AIAA 2000-0741,2000. [3] 潘旭,葛宁.带涡轮燃烧室的涡扇发动机设计点性能分析[J].燃气涡轮试验与研究,2007,20(3):34-38. PAN Xu,GE Ning.Parametric(on-design) analysis for a separate-exhaust turbofan engine with interstage turbine burner[J].Gas Turbine Experiment and Research,2007,20(3):34-38.(in Chinese) [4] 骆广琦,郑九洲,张发启.多级涡轮级间燃烧室发动机与常规涡轮喷气发动机性能对比研究[J].弹箭与制导学报,2009,29(1):162-165. LUO Guangqi,ZHENG Jiuzhou,ZHANG Faqi.Multiple turbine inter-stage burners turbofan engine performance research[J].Journal of Projectiles,Rockets,Missiles and Guidance.2009,29(1):162-165.(in Chinese) [5] 骆广琦,宋文艳,宋迪源.循环参数对涡轮级间燃烧室发动机性能影响[J].弹箭与制导学报,2009,29(5):152-154. LUO Guangqi,SONG Wenyan,SONG Diyuan.The influence of cycle parameters on inter-turbine burner turbofan engine performance[J].Journal of Projectiles,Rockets,Missiles and Guidance,2009,29(5):152-154.(in Chinese) [6] 孙泽晖,蔡元虎,屠秋野.带混排涡轮级间燃烧的涡扇发动机循环参数[J].推进技术,2010,31(2):139-142. SUN Zehui,CAI Yuanhu,TU Qiuye.Parametric cycle analysis of mixed exhaust turbofan with inter-stage turbine burner[J].Journal of Propulsion Technology,2010,31(2):139-142.(in Chinese) [7] Liew K H,Urip E,Yang S L,et al.A complete parametric cycle analysis of a turbofan with interstage turbine burner .AIAA 2003-0685,2003. [8] Liew K H,Urip E,Yang S L,et al.Performance cycle analysis of a two-spool,separate exhaust turbofan with interstage turbine burner .AIAA 2004-3311,2004. [9] Gorden C,Myron A H. Improvements in gas turbine performance through the use of multiple turbine inter-stage burners . AIAA 2004-374,2004. [10] Mawid M A,Park T W.Numerical analysis of inter-turbine burner (ITB) concepts for improved gas turbine engine performance .AIAA 2005-1162,2005. [11] Chiu Y T,King P S,Brien W F.A performance study of a super-cruise engine with isothermal combustion inside the turbine .AIAA-2005-4197,2005. [12] Lee A S,Singh R,Probert S D.Two-combustor engines' performances under design and off-design conditions .AIAA 2009-4838,2009.
点击查看大图
计量
- 文章访问数: 2073
- HTML浏览量: 1
- PDF量: 43
- 被引次数: 0