二冲程火花点火式发动机缸内压力测量方法的研究

IF 0.3 Q4 ENGINEERING, AEROSPACE SAE International Journal of Aerospace Pub Date : 2023-05-12 DOI:10.4271/01-17-01-0004
Joseph K. Ausserer, M. Polanka, Paul J. Litke, K. D. Grinstead
{"title":"二冲程火花点火式发动机缸内压力测量方法的研究","authors":"Joseph K. Ausserer, M. Polanka, Paul J. Litke, K. D. Grinstead","doi":"10.4271/01-17-01-0004","DOIUrl":null,"url":null,"abstract":"This work describes an investigation of measurement techniques for the indicated\n mean effective pressure (IMEP) on a 55 cc single-cylinder, 4.4 kW, two-stroke,\n spark ignition (SI) engine intended for use on Group 1 and Group 2 remotely\n piloted aircraft (RPAs). Three different sensors were used: two piezoelectric\n pressure transducers (one flush mount and one measuring spark plug) for\n measuring in-cylinder pressure and one capacitive sensor for determining the top\n dead center (TDC) position of the piston. The effort consisted of three\n objectives: to investigate the merits of a flush mount pressure transducer\n compared to a pressure transducer integrated into the spark plug, to perform a\n parametric analysis to characterize the effect of the variability in the engine\n test bench controls on the IMEP, and to determine the thermodynamic loss angle\n for the engine. The results indicate that as a spark plug, the measuring spark\n plug is not statistically different from the stock spark plug at the 95%\n confidence level. The results indicate a statistically significant, 4%\n difference in the measured IMEP between the pressure transducer in the measuring\n spark plug and the flush mount transducer. The results also suggest a\n statistically significant difference in performance between the modified and\n unmodified engine heads, verifying the suppositions of other researchers who\n suggested that even a small modification to a combustion chamber this size could\n measurably affect the engine performance. While run-to-run variation resulted in\n a 2% to 5% variation in IMEP, a sensitivity analysis determined that 1% to 3% of\n that variation arose from variability in the control variables, while the\n remainder was caused by variation in other engine operating parameters. Between\n 1000 rpm and 2000 rpm, where the engine was typically motored to determine the\n TDC, the thermodynamic loss angle was 0.3 crank angle degrees (CAD) to 0.7 CAD,\n larger than loss angles observed in automotive-sized gasoline engines. The\n results indicate that using tabulated thermodynamic loss angles to set the TDC\n location of the engine using a mono-directional peak pressure method would lead\n to a −1% to −2.5% bias in the IMEP.","PeriodicalId":44558,"journal":{"name":"SAE International Journal of Aerospace","volume":" ","pages":""},"PeriodicalIF":0.3000,"publicationDate":"2023-05-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Investigation of In-Cylinder Pressure Measurement Methods within a\\n Two-Stroke Spark Ignition Engine\",\"authors\":\"Joseph K. Ausserer, M. Polanka, Paul J. Litke, K. D. Grinstead\",\"doi\":\"10.4271/01-17-01-0004\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"This work describes an investigation of measurement techniques for the indicated\\n mean effective pressure (IMEP) on a 55 cc single-cylinder, 4.4 kW, two-stroke,\\n spark ignition (SI) engine intended for use on Group 1 and Group 2 remotely\\n piloted aircraft (RPAs). Three different sensors were used: two piezoelectric\\n pressure transducers (one flush mount and one measuring spark plug) for\\n measuring in-cylinder pressure and one capacitive sensor for determining the top\\n dead center (TDC) position of the piston. The effort consisted of three\\n objectives: to investigate the merits of a flush mount pressure transducer\\n compared to a pressure transducer integrated into the spark plug, to perform a\\n parametric analysis to characterize the effect of the variability in the engine\\n test bench controls on the IMEP, and to determine the thermodynamic loss angle\\n for the engine. The results indicate that as a spark plug, the measuring spark\\n plug is not statistically different from the stock spark plug at the 95%\\n confidence level. The results indicate a statistically significant, 4%\\n difference in the measured IMEP between the pressure transducer in the measuring\\n spark plug and the flush mount transducer. The results also suggest a\\n statistically significant difference in performance between the modified and\\n unmodified engine heads, verifying the suppositions of other researchers who\\n suggested that even a small modification to a combustion chamber this size could\\n measurably affect the engine performance. While run-to-run variation resulted in\\n a 2% to 5% variation in IMEP, a sensitivity analysis determined that 1% to 3% of\\n that variation arose from variability in the control variables, while the\\n remainder was caused by variation in other engine operating parameters. Between\\n 1000 rpm and 2000 rpm, where the engine was typically motored to determine the\\n TDC, the thermodynamic loss angle was 0.3 crank angle degrees (CAD) to 0.7 CAD,\\n larger than loss angles observed in automotive-sized gasoline engines. The\\n results indicate that using tabulated thermodynamic loss angles to set the TDC\\n location of the engine using a mono-directional peak pressure method would lead\\n to a −1% to −2.5% bias in the IMEP.\",\"PeriodicalId\":44558,\"journal\":{\"name\":\"SAE International Journal of Aerospace\",\"volume\":\" \",\"pages\":\"\"},\"PeriodicalIF\":0.3000,\"publicationDate\":\"2023-05-12\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"SAE International Journal of Aerospace\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.4271/01-17-01-0004\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q4\",\"JCRName\":\"ENGINEERING, AEROSPACE\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"SAE International Journal of Aerospace","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.4271/01-17-01-0004","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q4","JCRName":"ENGINEERING, AEROSPACE","Score":null,"Total":0}
引用次数: 0

摘要

本工作描述了用于第1组和第2组遥控飞机(RPA)的55 cc单缸、4.4 kW、二冲程火花点火式(SI)发动机的指示平均有效压力(IMEP)的测量技术研究。使用了三种不同的传感器:两个用于测量缸内压力的压电压力传感器(一个齐平安装和一个测量火花塞)和一个用于确定活塞上止点(TDC)位置的电容传感器。这项工作包括三个目标:研究嵌入式压力传感器与集成在火花塞中的压力传感器相比的优点,进行参数分析,以表征发动机试验台控制的可变性对IMEP的影响,并确定发动机的热力学损失角。结果表明,作为火花塞,在95%置信水平下,测量火花塞与库存火花塞没有统计学差异。结果表明,测量火花塞中的压力传感器和嵌入式传感器之间测量的IMEP存在4%的统计学显著差异。研究结果还表明,改进后的发动机缸盖和未改进的发动机缸盖之间的性能存在统计学上的显著差异,这验证了其他研究人员的假设,他们认为,即使对这种尺寸的燃烧室进行微小的修改,也会显著影响发动机性能。虽然运行间的变化导致IMEP变化2%至5%,但敏感性分析确定,1%至3%的变化是由控制变量的变化引起的,而其余的变化则是由其他发动机运行参数的变化引起。在1000rpm和2000rpm之间,其中发动机通常被驱动以确定TDC,热力学损失角为0.3曲轴转角(CAD)至0.7 CAD,大于在汽车尺寸的汽油发动机中观察到的损失角。结果表明,使用表中的热力学损失角,使用单向峰值压力法设置发动机的TDC位置,会导致IMEP出现−1%至−2.5%的偏差。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
查看原文
分享 分享
微信好友 朋友圈 QQ好友 复制链接
本刊更多论文
Investigation of In-Cylinder Pressure Measurement Methods within a Two-Stroke Spark Ignition Engine
This work describes an investigation of measurement techniques for the indicated mean effective pressure (IMEP) on a 55 cc single-cylinder, 4.4 kW, two-stroke, spark ignition (SI) engine intended for use on Group 1 and Group 2 remotely piloted aircraft (RPAs). Three different sensors were used: two piezoelectric pressure transducers (one flush mount and one measuring spark plug) for measuring in-cylinder pressure and one capacitive sensor for determining the top dead center (TDC) position of the piston. The effort consisted of three objectives: to investigate the merits of a flush mount pressure transducer compared to a pressure transducer integrated into the spark plug, to perform a parametric analysis to characterize the effect of the variability in the engine test bench controls on the IMEP, and to determine the thermodynamic loss angle for the engine. The results indicate that as a spark plug, the measuring spark plug is not statistically different from the stock spark plug at the 95% confidence level. The results indicate a statistically significant, 4% difference in the measured IMEP between the pressure transducer in the measuring spark plug and the flush mount transducer. The results also suggest a statistically significant difference in performance between the modified and unmodified engine heads, verifying the suppositions of other researchers who suggested that even a small modification to a combustion chamber this size could measurably affect the engine performance. While run-to-run variation resulted in a 2% to 5% variation in IMEP, a sensitivity analysis determined that 1% to 3% of that variation arose from variability in the control variables, while the remainder was caused by variation in other engine operating parameters. Between 1000 rpm and 2000 rpm, where the engine was typically motored to determine the TDC, the thermodynamic loss angle was 0.3 crank angle degrees (CAD) to 0.7 CAD, larger than loss angles observed in automotive-sized gasoline engines. The results indicate that using tabulated thermodynamic loss angles to set the TDC location of the engine using a mono-directional peak pressure method would lead to a −1% to −2.5% bias in the IMEP.
求助全文
通过发布文献求助,成功后即可免费获取论文全文。 去求助
来源期刊
SAE International Journal of Aerospace
SAE International Journal of Aerospace ENGINEERING, AEROSPACE-
CiteScore
0.70
自引率
0.00%
发文量
22
期刊最新文献
Computational Investigation of a Flexible Airframe Taxiing Over an Uneven Runway for Aircraft Vibration Testing Material Recognition Technology of Internal Loose Particles in Sealed Electronic Components Based on Random Forest External Synchronization of Distributed Redundant Flight Control Computers Reviewers Determination of the Heat-Controlled Accumulator Volume for the Two-Phase Thermal Control Systems of Spacecraft
×
引用
GB/T 7714-2015
复制
MLA
复制
APA
复制
导出至
BibTeX EndNote RefMan NoteFirst NoteExpress
×
×
提示
您的信息不完整,为了账户安全,请先补充。
现在去补充
×
提示
您因"违规操作"
具体请查看互助需知
我知道了
×
提示
现在去查看 取消
×
提示
确定
0
微信
客服QQ
Book学术公众号 扫码关注我们
反馈
×
意见反馈
请填写您的意见或建议
请填写您的手机或邮箱
已复制链接
已复制链接
快去分享给好友吧!
我知道了
×
扫码分享
扫码分享
Book学术官方微信
Book学术文献互助
Book学术文献互助群
群 号:481959085
Book学术
文献互助 智能选刊 最新文献 互助须知 联系我们:info@booksci.cn
Book学术提供免费学术资源搜索服务,方便国内外学者检索中英文文献。致力于提供最便捷和优质的服务体验。
Copyright © 2023 Book学术 All rights reserved.
ghs 京公网安备 11010802042870号 京ICP备2023020795号-1