Study on calculation of thrust characteristics of propulsive micro turboprop engine
-
摘要:
尾推式微型涡桨发动机主要由螺旋桨产生推力，喷管在产生剩余推力的同时会与螺旋桨产生复杂的气动干扰。为探究在这种气动干扰下尾推式微型涡桨发动机推力特性的变化规律，在计算上验证了MRF（移动参考系）方法在推进式微型涡桨发动机推力特性计算方面的可行性，开展了螺旋桨、喷管和短舱一体化构型的CFD（计算流体动力学）计算，得到了在地面慢车和巡航阶段时不同喷管压比、喷射角、螺旋桨转速和来流马赫数对发动机推力特性的影响规律。经分析发现：在地面状态下，喷射角为0°时，螺旋桨推力系数始终大于0.1，在同样压比下总推力最大可相差36%；喷射角为0°～60°时，螺旋桨推力系数随压比增大而减小；喷射角为90°时随压比的增大而增大。在巡航状态下，喷射角和压比对桨推力系数影响较小，桨推力系数随来流马赫数的增大而减小，随桨转速的增大而增大。两种状态下喷射角为0°时喷管剩余推力最大，获得的总推力最大，表现出良好的推力特性。
Abstract:The thrust of the propulsive micro turboprop engine was produced primarily by the propeller. Not only did the nozzle generate residual thrust, but also it could make complex aerodynamic interference with the propeller. In order to explore the variation of thrust characteristics of propulsive micro turboprop engines under interference, the feasibility of the MRF (moving reference frame) method in calculating thrust characteristics of propulsive micro turboprop engines was verified. The CFD (computational fluid dynamics) calculation for the integrated configuration of the propeller, nozzle and nacelle was conducted. The influences of different nozzle pressure ratios, injection angles, propeller speeds, and incoming Mach numbers on the thrust characteristics of the engine during the idling and cruise states were obtained. It was found that, in the ground state, when the injection angle was 0°, the thrust coefficient of the propeller was greater than 0.1, and the maximum difference of the total thrust can reach 36% under the same pressure ratio; when the injection angle was 0°—60°, the propeller thrust coefficient decreased with the pressure ratio, but increased at the injection angle of 90°. In the cruise state, the injection angle and pressure ratio had less influence on the thrust coefficient of the propeller. In contrast, the propeller thrust coefficient decreased with the incoming Mach number and increased with the propeller speed. When the injection angle was 0°, the nozzle’s remaining thrust was maximum, and the total thrust was maximum in these two states, showing good thrust characteristics.
-
Key words:
- propulsive /
- micro turboprop engine /
- propeller /
- nozzle /
- thrust characteristic
-
图 1 尾推式微型涡桨发动机螺旋桨、喷管和短舱模型
Figure 1. Propeller, nozzle and nacelle model of the propulsive micro turboprop engine
图 7 地面慢车基本状态下的压力和马赫数分布
Figure 7. Pressure and Mach number distribution in the basic state of ground idle
图 8 螺旋桨推力系数、喷管推力和总推力随NPR变化
Figure 8. Changes of the propeller thrust coefficient, the nozzle thrust and the total thrust with $ \text{NPR} $
图 10 不同喷射角$ \alpha $下的压力和马赫数分布
Figure 10. Pressure and Mach number distribution at different $ \alpha $
图 11 螺旋桨推力系数、喷管推力和总推力随转速$ {{N}} $的变化
Figure 11. Propeller thrust coefficient, the nozzle thrust and the total thrust at different $ {{N}} $
图 12 不同转速$ {{N}} $下的压力和马赫数分布
Figure 12. Pressure and Mach number distribution at different $ {{N}} $
图 13 螺旋桨推力系数和总推力随NPR和$ {{N}} $变化
Figure 13. Propeller thrust coefficient, the total thrust at different NPR and $ {{N}} $
图 14 不同NPR下的压力和马赫数分布
Figure 14. Pressure and Mach number distribution at different NPR
图 15 不同转速$ {{N}} $下的压力和马赫数分布
Figure 15. Pressure and Mach number distribution at different $ {{N}} $
图 16 螺旋桨推力系数和总推力随$ \alpha $和$ {{M}}{a_\infty } $变化
Figure 16. Propeller thrust coefficient, the total thrust at different $ \alpha $ and $ {{M}}{a_\infty } $
图 17 不同喷射角$ \alpha $下的压力和马赫数分布
Figure 17. Pressure and Mach number distribution at different $ \alpha $
图 18 不同$ {{M}}{a_\infty } $下的压力和马赫数分布
Figure 18. Pressure and Mach number distribution at different $ {{M}}{a_\infty } $
表 1 弦长比c/R随半径比r/R分布
Table 1. Chord length ratio c/R distribution with Radius ratio r/R
r/R c/R 0.1 0.133 0.3 0.186 0.5 0.220 0.7 0.212 0.9 0.088 
下载: 导出CSV
表 2 网格无关性验证
Table 2. Grid-independent validation
网格
数量/万螺旋桨推力 总推力 推力/N 相对误差/% 推力/N 相对误差/% 416 499.6 0.83 504.5 0.78 475 495.5 0.28 500.6 0.28 507 494.1 0.18 499.2 0.10 566 493.2 0 498.7 0
下载: 导出CSV
表 3 螺旋桨工作状态
Table 3. Operating state of the propeller
参数 数值 转速/（r/min） 8000 前进比 0.595 迎角/（°） 0 来流速度/（m/s） 30.2
下载: 导出CSV
表 4 计算结果与试验结果对比
Table 4. Comparison of the calculated and the test results
参数 计算值 试验值 相对误差/% 推力系数$ {{{C}}_{{T}}} $ 1.34 1.4 4.3 扭矩系数CQ 0.251 0.261 3.8 螺旋桨推力占比 74.6 73 2.2
下载: 导出CSV
表 5 基本工作状态
Table 5. Basic working status
工况 来流马赫数 螺旋桨
转速/（r/min）喷管压比 喷射角/（°） 桨距角/（°） 飞行高度/m 大气压/kPa 远场温度/K 地面慢车 0.01 2000 1.03 0 20 0 101.325 300 巡航 0.4 4000 1.03 0 50 5000 54.048 255.7
下载: 导出CSV
-
[1] STUERMER A, RAKOWITZ M. Unsteady simulation of a transport aircraft propeller using MEGAFLOW: RTO-MP-AVT-123 [R]. Neuilly-sur-Seine, France: RTO (Research Testing Organization), 2005. [2] STUERMER A. Unsteady CFD simulations of propeller installation effects: AIAA 2006-4969 [R]. Sacramento, US: AIAA, 2006. [3] ROOSENBOOM E W M, STÜRMER A, SCHRÖDER A. Advanced experimental and numerical validation and analysis of propeller slipstream flows[J]. Journal of Aircraft, 2010, 47(1): 284-291. doi: 10.2514/1.45961 [4] 史文博, 李杰. 对转螺旋桨流场气动干扰数值模拟[J]. 航空动力学报, 2019, 34(4): 829-837. SHI Wenbo, LI Jie. Numerical simulation of contra-rotating propeller flowfield aerodynamic interactions[J]. Journal of Aerospace Power, 2019, 34(4): 829-837. (in ChineseSHI Wenbo, LI Jie. Numerical simulation of contra-rotating propeller flowfield aerodynamic interactions[J]. Journal of Aerospace Power, 2019, 34(4): 829-837. (in Chinese) [5] 陈荣钱, 王旭, 尤延铖. 短舱对螺旋桨滑流影响的IDDES数值模拟[J]. 航空学报, 2016, 37(6): 1851-1860. CHEN Rongqian, WANG Xu, YOU Yancheng. Numerical simulation of nacelle’s effects on propeller slipstream based on IDDES model[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(6): 1851-1860. (in ChineseCHEN Rongqian, WANG Xu, YOU Yancheng. Numerical simulation of nacelle’s effects on propeller slipstream based on IDDES model[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(6): 1851-1860. (in Chinese) [6] 杨小川, 王运涛, 王光学, 等. 螺旋桨非定常滑流的高效数值模拟研究[J]. 空气动力学学报, 2014, 32(3): 289-294. YANG Xiaochuan, WANG Yuntao, WANG Guangxue, et al. Bumerical simulation of unsteady propeller slipstream[J]. Acta Aerodynamica Sinica, 2014, 32(3): 289-294. (in ChineseYANG Xiaochuan, WANG Yuntao, WANG Guangxue, et al. Bumerical simulation of unsteady propeller slipstream[J]. Acta Aerodynamica Sinica, 2014, 32(3): 289-294. (in Chinese) [7] BOUSQUET J M, GARDAREIN P. Improvements on computations of high speed propeller unsteady aerodynamics[J]. Aerospace Science and Technology, 2003, 7(6): 465-472. doi: 10.1016/S1270-9638(03)00046-4 [8] VELDHUIS L, NEBIOLO S. Analysis of calculated and measured wake characteristics of a propeller-wing model: AIAA2000-908 [R]. Reston, US: AIAA, 2000. [9] LOPEZ-DIEZ A, RUIZ-CALAVERA L, CASTILLO-CALVO J, et al. Front end optimization of high speed turboprop engines: AIAA2005-4204[R]. Reston, US: AIAA, 2005. [10] VELDHUIS L L M, NEBIOLO S. A propeller-integration study comparing experiment data with numerical flow solutions based on the Navier-Stokes equations[C]// Proceedings of International Council of the Aeronautical Sciences (ICAS) 2000 Congress. Harrogate, UK: ICAS, 2000: 264.1-264.9. [11] FERRARO G, KIPOUROS T, SAVILL A M, et al. Propeller-wing interaction prediction for early design: AIAA2014-0564[R]. Reston, US: AIAA, 2014. [12] 周诗睿, 李博, 周杨, 等. 螺旋桨滑流对发动机进气道气动性能的影响[J]. 航空动力学报, 2019, 34(6): 1322-1333. ZHOU Shirui, LI Bo, ZHOU Yang, et al. Aerodynamic performance influence of propeller slipstream on engine intake[J]. Journal of Aerospace Power, 2019, 34(6): 1322-1333. (in ChineseZHOU Shirui, LI Bo, ZHOU Yang, et al. Aerodynamic performance influence of propeller slipstream on engine intake[J]. Journal of Aerospace Power, 2019, 34(6): 1322-1333. (in Chinese) [13] 夏贞锋, 杨永. 螺旋桨滑流与机翼气动干扰的非定常数值模拟[J]. 航空学报, 2011, 32(7): 1195-1201. XIA Zhenfeng, YANG Yong. Unsteady numerical simulation of interaction effects of propeller and wing[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(7): 1195-1201. (in ChineseXIA Zhenfeng, YANG Yong. Unsteady numerical simulation of interaction effects of propeller and wing[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(7): 1195-1201. (in Chinese) [14] 陈广强, 白鹏, 詹慧玲, 等. 一种推进式螺旋桨无人机滑流效应影响研究[J]. 空气动力学学报, 2015, 33(4): 554-562. CHEN Guangqiang, BAI Peng, ZHAN Huiling, et al. Numerical simulation study on propeller slipstream effect on unmanned air vehicle with propeller engine[J]. Acta Aerodynamica Sinica, 2015, 33(4): 554-562. (in Chinese doi: 10.7638/kqdlxxb-2014.0013CHEN Guangqiang, BAI Peng, ZHAN Huiling, et al. Numerical simulation study on propeller slipstream effect on unmanned air vehicle with propeller engine[J]. Acta Aerodynamica Sinica, 2015, 33(4): 554-562. (in Chinese) doi: 10.7638/kqdlxxb-2014.0013 [15] 韩俊豪, 王云, 张国喜. 机翼对后置螺旋桨性能影响的研究[J]. 南昌航空大学学报(自然科学版), 2014, 28(4): 55-59. HAN Junhao, WANG Yun, ZHANG Guoxi. Influence of the wing upon performance of after mounted propeller[J]. Journal of Nanchang Hangkong University (Natural Sciences), 2014, 28(4): 55-59. (in ChineseHAN Junhao, WANG Yun, ZHANG Guoxi. Influence of the wing upon performance of after mounted propeller[J]. Journal of Nanchang Hangkong University (Natural Sciences), 2014, 28(4): 55-59. (in Chinese) [16] 昝丙合, 何淼, 朱建勇. 高速直升机尾推螺旋桨气动设计研究[J]. 排灌机械工程学报, 2022, 40(3): 282-286, 301. ZAN Binghe, HE Miao, ZHU Jianyong. Research on aerodynamic design of tail-thrust propeller of high-speed helicopter[J]. Journal of Drainage and Irrigation Machinery Engineering, 2022, 40(3): 282-286, 301. (in ChineseZAN Binghe, HE Miao, ZHU Jianyong. Research on aerodynamic design of tail-thrust propeller of high-speed helicopter[J]. Journal of Drainage and Irrigation Machinery Engineering, 2022, 40(3): 282-286, 301. (in Chinese) [17] 车海峰, 叶靓, 邱福生, 等. 机身形状对共轴尾推螺旋桨气动干扰影响研究[J]. 气动研究与试验, 2023, 1(6): 41-50. CHE Haifeng, YE Liang, QIU Fusheng, et al. Research on aerodynamic interference influence of airframe shape on coaxial tail propeller[J]. Aerodynamic Research & Experiment, 2023, 1(6): 41-50 (in ChineseCHE Haifeng, YE Liang, QIU Fusheng, et al. Research on aerodynamic interference influence of airframe shape on coaxial tail propeller[J]. Aerodynamic Research & Experiment, 2023, 1(6): 41-50 (in Chinese) [18] GRUNWAI. D K J, GOODSON K W. Aerodynamic loads on an isolated shrouded propeller configuration for angles of attack from −10° to 110°: NASA-TN-D-995[R]. Washington DC: NASA, 1962. -
点击查看大图
计量
- 文章访问数: 646
- HTML浏览量: 516
- PDF量: 46
- 被引次数: 0