Experiment on influence of front/after-mounted propeller on turboprop engine performance
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摘要: 基于一款15 kW涡桨发动机,构建了带偏置进气道的前/后置螺旋桨整机试验台,探究了前/后置螺旋桨流动特性对涡桨发动机性能的影响规律。研究结果表明:随着燃气涡轮转速的增加,螺旋桨滑流增压效果增强、进气道内气流损失增加,其中相对换算转速64%及88%状态滑流增压效果分别为0.35%及0.7%,综合表现为前置状态下螺旋桨/进气道的综合总压恢复系数基本维持在100%;受制于前置螺旋桨滑流增压效果与外置传输轴功率损失的综合影响,在相同燃气涡轮转速下,前/后置状态的发动机拉力基本一致,但后置状态的螺旋桨转速增加2.8%~4%、出口排气温度增加11~22 ℃;相比于后置状态正上方压力相对偏高的图谱分布,前置状态下气流在进气道内沿螺旋桨旋转方向往右下角方向进行堆积,进气道出口呈现右下角压力高、左上角压力低的图谱分布,总压畸变指数有所降低。Abstract: Based on a 15 kW turboprop engine,a test rig for a biased inlet adopting a front/after-mounted propeller configuration was built.And the influence of the front/after-mounted propeller configurations on the performance of turboprop engine was investigated.The results showed that:with the increase of the gas turbine speed,the pressurization effect of the propeller slipstream was enhanced and the airflow loss in the inlet duct increased.The pressurization effect of propeller slipstream was 0.35% and 0.7% at the relative corrected speed of 64% and 88%,respectively.It showed that when adopting the front-mounted configuration,the total pressure recovery coefficient of propeller/intake duct system was basically maintained at 100%;limited by both the slipstream pressurization effect from the front-mounted propeller and the power loss of the external transmission shaft,the engine pull was almost the same at the same gas turbine speed no matter the propeller was mounted front or rear,but the speed of the propeller in the rear position increased by 2.8%-4%,and the outlet exhaust temperature increased by 11-22 ℃;For the after-mounted propeller configuration,the distortion pattern was characterized by a relatively high pressure distribution at its upper part.In contrast,for the front-mounted configuration,since the airflow accumulated at the lower right corner along the direction of the propeller rotation,the distortion pattern at the outlet of inlet duct showed a distribution of high pressure in the lower right corner and low pressure in the upper left corner.And the total pressure distortion index decreased.
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Key words:
- propeller /
- slipstream /
- turboprop engine /
- inlet /
- pressure distortion
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[1] 刘沛清.空气螺旋桨理论及其应用[M].北京:北京航空航天大学出版社,2006. [2] 周辉华.国外涡桨发动机的发展[J].航空科学技术,2013,1:18-22. [3] 夏天乾.可变桨距微型涡桨发动机控制系统设计与试验研究[D].南京:南京航空航天大学,2019. [4] ALEXIOU A,FRANTZIS C,ARETAKIS N,et al.Contra-rotating propeller modelling for open rotor engine performance simulations[R].ASME Paper GT2012-69232,2016. [5] SILVA V T,BRINGHENTI C,TOMITA J T,et al.A propeller model for steady-state and transient performance prediction of turboprop and counter-rotating open rotor engines[J].Journal of Engineering for Gas Turbines and Power,2018,140(7):071201.1-071201.13. [6] 温占永,罗洋.中空长航时无人机恒速螺旋桨与发动机匹配研究[J].航空工程进展,2020,11(5):672-678. [7] 史永运.螺旋桨动力系统桨发匹配技术研究[D].南京:南京航空航天大学.2017. [8] 田超.航空涡桨发动机建模与控制的仿真研究[D].南京:南京航空航天大学,2010. [9] PAKMEHR M,FITZGERALD N,FERON E,et al.Physics-based dynamic modeling of a turboshaft engine driving a variable pitch propeller[J].Journal of Propulsion and Power,2016,32(1):646-658. [10] LOPEZ-DIEZ A,RUIZ-CALAVERA L,CASTILLO-CALVO J,et al.Front end optimization of high speed turboprop engines[R].AIAA 2005-4204,2005. [11] RUIZ-CALAVERA L,FUNES-SEBASTIAN D,PERDONES- DIAZ D.Powered model wind tunnel tests of a high-offset subsonic turboprop air intake[R].AIAA 2010-6502,2010. [12] 罗天一,单鹏,孟斐,等.螺旋桨-自由涡轮涡桨发动机稳态/过渡态数值模拟[J].航空动力学报,2017,32(5):1176-1182 [13] 田超,黄向华,邓志伟.涡轮螺旋桨发动机建模与控制仿真[J].航空动力学报,2010,25(11):2599-2605. [14] 刘婧妮.先进涡轴/涡桨发动机总体性能设计研究[D].南京:南京航空航天大学,2015. [15] 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. [16] 潘鑫智.螺旋桨与发动机短舱/进气道的气动影响研究[D].南京:南京航空航天大学,2014. [17] 李博,梁德旺,黄国平.基于等效盘模型的滑流对涡桨飞机气动性能的影响[J].航空学报,2008,29(4):845-852. [18] 靖建朋,郭荣伟.弹用S弯进气道气动性能试验[J].航空动力学报,2009,24(9):2085-2090.
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