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。
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.
作者
韦宇卿
郭峰
朱剑锋
李伟
黄兴
WEI Yuqing;GUO Feng;ZHU Jianfeng;LI Wei;HUANG Xing(School of Aerospace Engineering,Xiamen University,Xiamen Fujian 361102,China;Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2022年第1期165-172,共8页
Journal of Aerospace Power
基金
中国航发自主创新专项资金项目(ZZCX-2018-017)。
关键词
螺旋桨
滑流
涡桨发动机
进气道
压力畸变
propeller
slipstream
turboprop engine
inlet
pressure distortion
