Overall performance study on turboshaft engine with inter-stage turbine burner
-
摘要:
为研究级间燃烧技术（ITB）对涡轴发动机总体性能的影响，利用Visual C++（VC）平台，采用部件级建模法，建立了级间燃烧涡轴发动机变比热仿真计算模型，并通过仿真对比分析了在不同工作循环参数匹配条件下发动机性能的变化。结果表明：主燃烧室出口总温与级间燃烧回热度对燃油消耗率的影响较大，当主燃烧室出口总温增加500 K，级间燃烧由关闭至全开状态，燃油消耗率的相对增幅下降了9.24%；在节流特性下，随着发动机核心机相对转速降低，开启级间燃烧对输出功率的提升幅度将减小；在高度特性下，随着飞行高度的增加，开启级间燃烧燃油消耗率降低的幅度将高于常规循环涡轴发动机；在温度特性下，随着大气温度的增加，开启级间燃烧燃油消耗率的增加幅度将高于常规循环涡轴发动机。
Abstract:To study the impact of inter-stage turbine burner (ITB) technology on the overall performance of turboshaft engine, a simulation model of variable specific heat was established using the component-level modeling method on the Visual C++ (VC) platform. Through simulation and comparative analysis, changes in engine performance were investigated under different operating cycle parameter matching conditions. The results indicated that the total temperature at the exit of the main combustion chamber and the ITB reheating had a significant influence on fuel consumption. When the total temperature at the exit of the main combustion chamber increased by 500 K and the ITB transited from closed to fully open state, the relative increase in fuel consumption decreased by 9.24%. Under throttling conditions, as the relative rotational speed of the engine core decreased, the magnitude of power output improvement from activating ITB decreased. Under altitude conditions, with increase of the flight altitude, the reduction in fuel consumption due to ITB was greater than that in a conventional turboshaft engine. Under temperature conditions, as the ambient atmospheric temperature increased, the increase in fuel consumption due to ITB was higher compared with a conventional turboshaft engine.
-
图 1 级间燃烧涡轴发动机模型示意图
Figure 1. Schematic diagram of inter-turbine burner turboshaft engine model
图 2 设计点性能随压气机增压比的变化
Figure 2. Variation of design point performance with pressure ratio of compressor
图 3 燃油质量流量随压气机增压比的变化
Figure 3. Variation of fuel mass flow rate with pressure ratio of compressor
图 4 热效率与动力涡轮相关参数随增压比的变化
Figure 4. Variation of thermal efficiency and power turbine-related parameters with pressure ratio
图 5 设计点总体性能随主燃烧室出口总温的变化
Figure 5. Variation of design point overall performance with exit total temperature of main combustion chamber
图 6 热效率与涡轮相关参数随主燃烧室出口总温的变化
Figure 6. Variation of thermal efficiency and turbine-related parameters with exit total temperature of main combustion chamber
图 7 两种循环参数共同作用下设计点性能的变化
Figure 7. Variation of design point performance under combined influence of two cycle parameters
图 8 设计点总体性能随压气机增压比与级间燃烧回热度的变化
Figure 8. Variation of design point overall performance with both compressor pressure ratio and inter-stage combustion reheating degree
图 9 设计点总体性能随主燃烧室出口总温与级间燃烧回热度的变化
Figure 9. Variation of design point overall performance with both main combustion chamber exit total temperature and inter-stage combustion reheating degree
图 10 加入级间燃烧后输出功率与燃油消耗率增长率随级间燃烧室总压恢复系数的变化
Figure 10. Variation of output power and fuel consumption rate growth rate with inter-stage combustion chamber total pressure recovery factor after introduction of inter-stage combustion
图 11 加入级间燃烧前后发动机节流特性对比
Figure 11. Comparison of engine throttling characteristics before and after introduction of inter-stage combustion
图 12 燃气涡轮出口相关参数随核心机转子相对转速变化
Figure 12. Variation of gas turbine outlet-related parameters with relative speed of core engine rotor
图 13 级间燃烧相关参数随核心机转子相对转速变化
Figure 13. Variation of inter-stage combustion-related parameters with relative speed of core engine rotor
图 14 加入级间燃烧前后发动机高度特性对比
Figure 14. Comparison of engine altitude characteristics before and after introduction of inter-stage combustion
图 15 燃气涡轮出口相关参数随飞行高度变化
Figure 15. Variation of gas turbine outlet-related parameters with flight altitude
图 16 动力涡轮出口相关参数随飞行高度变化
Figure 16. Variation of power turbine outlet-related parameters with flight altitude
图 17 加入级间燃烧前后发动机温度特性对比
Figure 17. Comparison of engine temperature characteristics before and after introduction of inter-stage combustion
图 18 燃气涡轮出口相关参数随大气温度变化
Figure 18. Variation of gas turbine outlet-related parameters with ambient atmospheric temperature
图 19 动力涡轮出口相关参数随大气温度变化
Figure 19. Variation of power turbine outlet-related parameters with ambient atmospheric temperature
表 1 模型站位标号
Table 1. Model station label
项目 站位 远前方气流截面 0 进气道入口截面 1 进气道出口截面 2 增压级出口截面 24 高压压气机入口截面 25 高压压气机出口截面 3 主燃烧室出口截面 4 燃气涡轮出口截面 45 动力涡轮入口截面 47 动力涡轮出口截面 5 排气管出口截面 8 
下载: 导出CSV
表 2 部分模型计算输入参数
Table 2. Partial model calculation input parameters
参数 数值 发动机进口换算质量流量/（kg/s） 8.8775 进气道总压恢复系数 0.98 增压级增压比 1.737 高压压气机增压比 5.237 主燃烧室出口总温/K 1190 燃气涡轮等熵效率 0.91 动力涡轮等熵效率 0.94 主燃烧室总压恢复系数 0.98 增压级等熵效率 0.86 高压压气机等熵效率 0.86 级间燃烧效率 0.998 级间燃烧室总压恢复系数 0.98
下载: 导出CSV
表 3 级间燃烧涡轴发动机仿真程序计算结果验证
Table 3. Validation of simulation program results for inter-turbine burner turboshaft engine
状态 参数 数值 相对
误差/%Gasturb VC程序 设计点 输出功率/kW 2281.2 2281.5 0.01315 燃油消耗率/
（kg/（kW∙h））0.3331 0.3370 1.17082 非设计点 输出功率/kW 2281.2 2281.3 0.00438 燃油消耗率/
（kg/（kW∙h））0.3331 0.3370 1.17082
下载: 导出CSV
表 4 涡轴发动机加入级间燃烧前后设计点性能对比
Table 4. Comparison of design point performance before and after incorporation of inter-stage turbine burner in turboshaft engine
参数 数值 变化率/% 未加入级间 加入级间 输出功率/kW 1768.98 2281.53 28.97 燃油消耗率/
（kg/（kW∙h））0.298809 0.337014 12.79
下载: 导出CSV
表 5 加入级间燃烧前后热效率与动力涡轮出口总温对比
Table 5. Comparison of thermal efficiency and total temperature at outlet of power turbine before and after inter-stage turbine burner
参数 数值 变化率/% 未加入级间 加入级间 $T_5^* $/K 755.63 972.78 28.74 热效率 0.2808 0.2490 −11.34
下载: 导出CSV
表 6 发动机最佳增压比与最经济增压比对应性能参数
Table 6. Performance parameters corresponding to optimal pressure ratio and the most economical pressure ratio of engine
项目 增压比 输出
功率/kW燃油消耗率/
（kg/（kW∙h））最佳增压比 13.669 2372.28 0.324723 最经济增压比 13.553 2372.23 0.324722
下载: 导出CSV
表 7 调节增压比后发动机性能提升幅度
Table 7. Extent of engine performance improvement after adjusting pressure ratio
状态 参数 数值 变化率/% 常规循环
设计点输出功率/kW 1768.98 34.10 燃油消耗率/
（kg/（kW∙h））0.298800 8.68 级间燃烧
设计点输出功率/kW 2281.53 3.98 燃油消耗率/
（kg/（kW∙h））0.337014 −3.64
下载: 导出CSV
表 8 最经济燃烧室出口总温对应发动机性能参数
Table 8. Engine performance parameters corresponding to the most economical combustion chamber exit total temperature
项目 最经济
$T_4^* $/K输出
功率/kW燃油消耗率/
（kg/（kW∙h））不带级间燃烧 1950 4988.478 0.268882 带级间燃烧 2130 6503.235 0.280230
下载: 导出CSV
表 9 调节主燃烧室出口总温后发动机性能提升幅度
Table 9. Extent of engine performance improvement after adjusting exit total temperature of main combustion chamber
状态 项目 数值 变化率/% 常规循环
设计点输出功率/kW 1768.98 267.63 燃油消耗率/
（kg/（kW∙h））0.298800 −6.21 级间燃烧
设计点输出功率/kW 2281.53 185.04 燃油消耗率/
（kg/（kW∙h））0.337014 −16.85
下载: 导出CSV
表 10 调节两种工作循环参数后发动机性能提升幅度
Table 10. Extent of engine performance improvement after adjusting two operational cycle parameters
状态 项目 数值 变化率/% 常规循环
设计点输出功率/kW 1768.98 263.20 燃油消耗率/
（kg/（kW∙h））0.298800 −25.72 级间燃烧
设计点输出功率/kW 2281.53 181.61 燃油消耗率/
（kg/（kW∙h））0.337014 −34.14
下载: 导出CSV
-
[1] RAMOHALLI K. Isothermal combustion for improved efficiencies[R]. San Diego,US: 23rd Joint Propulsion Conference,1987. [2] JOOS F,BRUNNER P,SCHULTE-WERNING B,et al. Development of the sequential combustion system for the ABB GT24/GT26 gas turbine family[J]. ABB Review,1998(4): 4-16. [3] SIRIGNANO W P,DELPLANQUE J,LIU F,et al. Selected challenges in jet and rocket engine combustion research[R]. AIAA-1997-2701,1997. [4] 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. doi: 10.2514/2.5398 [5] FRUTSCHI H U. Advanced cycle system with new GT24 and GT26 gas turbines: historical background[J]. ABB Review,1994(1): 20-25. [6] NEUHOFF H,THOREN K. GT24 and GT26 gas turbines: sequential combustion and the key to high efficiencies[J]. ABB Review,1994(2): 4-7. [7] SEKAR B,THORNBURG H,BRIONES A,et al. Effect of trapped vortex combustion with radial vane cavity arrangements on predicted inter-turbine burner performance[R]. AIAA-2009-4603,2009. [8] SIRIGNANO W,DUNN-RANKIN D,LIU Feng,et al. Turbine burners: flameholding in accelerating flow[R]. AIAA-2009-5410,2009. [9] 齐少军,葛爱学,蔡元虎,等. 用高低压涡轮间补燃提高双轴涡扇发动机性能[J]. 推进技术,2002,23(6): 453-456. QI Shaojun,GE Aixue,CAI Yuanhu,et al. Application of after-burning between high and low turbines to improve performance of two-spool turbofan engine[J]. Journal of Propulsion Technology,2002,23(6): 453-456. (in Chinese doi: 10.3321/j.issn:1001-4055.2002.06.004QI Shaojun, GE Aixue, CAI Yuanhu, et al. Application of after-burning between high and low turbines to improve performance of two-spool turbofan engine[J]. Journal of Propulsion Technology, 2002, 23(6): 453-456. (in Chinese) doi: 10.3321/j.issn:1001-4055.2002.06.004 [10] 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 doi: 10.3969/j.issn.1673-9728.2009.01.047LUO 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) doi: 10.3969/j.issn.1673-9728.2009.01.047 [11] 屠秋野,孙泽晖,牟锦辉,等. 带涡轮级间次燃烧室混排涡扇发动机的超声速性能研究[J]. 航空计算技术,2010,40(4): 14-17. TU Qiuye,SUN Zehui,MOU Jinhui,et al. Super-sonic performance research on mixed exhaust turbofan engine with inter-stage turbine burner[J]. Aeronautical Computing Technique,2010,40(4): 14-17. (in Chinese doi: 10.3969/j.issn.1671-654X.2010.04.005TU Qiuye, SUN Zehui, MOU Jinhui, et al. Super-sonic performance research on mixed exhaust turbofan engine with inter-stage turbine burner[J]. Aeronautical Computing Technique, 2010, 40(4): 14-17. (in Chinese) doi: 10.3969/j.issn.1671-654X.2010.04.005 [12] PELLEGRINI A,NIKOLAIDIS T,PACHIDIS V,et al. On the performance simulation of inter-stage turbine reheat[J]. Applied Thermal Engineering,2017,113: 544-553. [13] YIN Feijia,RAO A G. A review of gas turbine engine with inter-stage turbine burner[J]. Progress in Aerospace Sciences,2020,121: 100695. [14] 彭友梅. 苏联/俄罗斯/乌克兰航空发动机的发展[M]. 北京: 航空工业出版社,2015. [15] 方骁远,邢菲,徐磊磊,等. 三种航空燃气轮机加入级间燃烧室后性能变化浅析[J]. 推进技术,2013,34(11): 1513-1519. FANG Xiaoyuan,XING Fei,XU Leilei,et al. Performance analysis of three kinds of aero-engine with inter-stage turbine burner[J]. Journal of Propulsion Technology,2013,34(11): 1513-1519. (in ChineseFANG Xiaoyuan, XING Fei, XU Leilei, et al. Performance analysis of three kinds of aero-engine with inter-stage turbine burner[J]. Journal of Propulsion Technology, 2013, 34(11): 1513-1519. (in Chinese) [16] LIEW K H,URIP E,YANG S L. Parametric cycle analysis of a turbofan engine with an interstage turbine burner[J]. Journal of Propulsion and Power,2005,21(3): 546-551. [17] 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 ChineseLUO 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) [18] 潘旭. 某新型双燃烧室涡轴发动机总体性能研究[D]. 南京: 南京航空航天大学,2008. PAN Xu. Performance cycle analysis for a turboshaft engine with interstage turbine burner[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2008. (in ChinesePAN Xu. Performance cycle analysis for a turboshaft engine with interstage turbine burner[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2008. (in Chinese) -
点击查看大图
计量
- 文章访问数: 427
- HTML浏览量: 490
- PDF量: 47
- 被引次数: 0