二冲程点燃式航空煤油发动机燃油消耗率及氮氧化物排放特性分析  

Analysis of Fuel Consumption Rate and Nitrogen Oxide Emission Characteristics of a Two-Stroke Spark-Ignition Aviation Kerosene Engine

作　　者：刘国满[1] 盛敬[1] 贝太学 刘锐 LIU Guo-man;SHENG Jing;BEI Tai-xue;LIU Rui(Jiangxi Province Key Laboratory of Precision Drive and Control,Nanchang Institute of Technology,Jiangxi Nanchang 330099,China;School of Mechanical and Electronic Engineering,Shandong Jianzhu University,Shandong Ji'nan 250101,China;School of Mechanical and Power Engineering,Nanjing Tech University,Jiangsu Nanjing 211816,China)

机构地区：[1]南昌工程学院江西省精密驱动与控制重点实验室,江西南昌330099 [2]山东建筑大学机电工程学院,山东济南250101 [3]南京工业大学机械与动力工程学院,江苏南京211816

出　　处：《机械设计与制造》2023年第3期203-206,211,共5页Machinery Design & Manufacture

基　　金：江西省教育厅科学技术研究项目(GJJ170989);国家自然基金项目(51865031);国家留学基金委资助(201808360039)。

摘　　要：针对某二冲程火花点火式活塞发动机燃烧航空煤油时燃油消耗率及氮氧化物排放特性的研究,采用GT-Power软件进行了数值模拟分析。首先建立了该发动机的整机模型,并利用发动机转速为6000r/min时的全负荷工况的缸内压力的数值模拟结果以及在3500r/min到6500r/min转速范围内的扭矩及功率等数值模拟结果分别跟试验数据进行对比分析,验证了GT-Power数值模拟计算模型的正确性。然后采用该模型对该发动机工作过程中的压缩比、空燃比、点火提前角、进气压力、进气温度等参数的变化对燃油消耗率以及氮氧化物生成量的影响进行了模拟计算。结果表明:在6000r/min工况下,压缩比增大使燃油消耗率降低,进气压力和进气温度增大均使得燃油消耗率升高,空燃比和点火提前角增大均使燃油消耗率呈现出先减小后增大的特点,燃油消耗率在空燃比为15.5和点火提前角为25°CA时出现了极值点;压缩比、进气压力、进气温度和点火提前角增大均使氮氧化物生成量增多,空燃比增大使得氮氧化物生成量出现了先增多后减少的现象,在空燃比为15.5时氮氧化物生成量达到峰值。In order to study the fuel consumption rate andNitrogen Oxide emission characteristics of a two-stroke spark-ignition piston engine burning aviation kerosene,the GT-Power software was used for numerical simulation analysis. Firstly,the complete model of the engine was established. The numerical simulation results of the cylinder pressure under full load at the engine speed of 6000r/min and the numerical simulation results of the torque and power within the range of 3500r/min to 6500r/min were compared with the test data respectively,thus verifying the correctness of the numerical simulation model of GT-Power. Then the effects of compression ratio,air-fuel ratio,ignition advance angle,inlet pressure,inlet temperature and other parameters on fuel consumption rate and Nitrogen Oxide production were simulated by using the model. The results showed that:under the condition of 6000r/min,the increase of compression ratio reduces the fuel consumption rate;the increase of inlet pressure and inlet temperature both increases the fuel consumption rate;the increase of air-fuel ratio and ignition advance angle both first reduces and then increases the fuel consumption rate. When the air-fuel ratio is 15.5 and the ignition advance angle is 25°CA,the extreme point of fuel consumption appears. The increase of compression ratio,inlet pressure,inlet temperature and ignition advance angle all led to the increase of Nitrogen Oxide production,while the increase of air-fuel ratio led to the phenomenon that Nitrogen Oxide production first increased and then decreased. When the air-fuel ratio was 15.5,Nitrogen Oxide production reached its peak value.

关 键 词：航空煤油发动机 燃油消耗率 氮氧化物生成量 GT-POWER 数值模拟 

分 类 号：TH16[机械工程—机械制造及自动化] V233.7[航空宇航科学与技术—航空宇航推进理论与工程]