Ayşe Nur Dişlitaş, Bilge Albayrak Çeper, Melih Yıldız
{"title":"使用参数回路分析涡轮风扇发动机","authors":"Ayşe Nur Dişlitaş, Bilge Albayrak Çeper, Melih Yıldız","doi":"10.1108/aeat-01-2023-0021","DOIUrl":null,"url":null,"abstract":"<h3>Purpose</h3>\n<p>In this study, the performance analysis of the split flow turbofan engine with afterburners has been examined using the parametric cycle analysis method. The purpose of this study is to examine how engine performance is impacted by design parameters and flight ambient values and to develop a software in this context.</p><!--/ Abstract__block -->\n<h3>Design/methodology/approach</h3>\n<p>Software has been developed using the open-source PYTHON programming language to perform performance analysis. Mach number, compressor/fan pressure ratio, bypass ratio and density were used as parameters. The effects of these variables on engine performance parameters were investigated.</p><!--/ Abstract__block -->\n<h3>Findings</h3>\n<p>Parametric cycle analysis has been calculated for different flight conditions in the range of 0–2 M and 0–15,000 m altitude for turbofan engines. With this study, basic data were obtained to optimize according to targeted flight conditions.</p><!--/ Abstract__block -->\n<h3>Practical implications</h3>\n<p>As a result of the performance analysis, the association between the flight conditions and design parameters of engine were determined. A software has been developed that can be used in the design of supersonic gas turbine engines for fast and easy simulation of the design parameters.</p><!--/ Abstract__block -->\n<h3>Originality/value</h3>\n<p>The variables used in the literature have been analyzed, and the results of the studies have been incorporated into the developed software, which can be used in innovative engine design. Software is capable to be developed further with the integration of new algorithms and models.</p><!--/ Abstract__block -->","PeriodicalId":55540,"journal":{"name":"Aircraft Engineering and Aerospace Technology","volume":"40 1","pages":""},"PeriodicalIF":1.2000,"publicationDate":"2023-12-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Analysis of a turbofan engine using a parametric loop\",\"authors\":\"Ayşe Nur Dişlitaş, Bilge Albayrak Çeper, Melih Yıldız\",\"doi\":\"10.1108/aeat-01-2023-0021\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"<h3>Purpose</h3>\\n<p>In this study, the performance analysis of the split flow turbofan engine with afterburners has been examined using the parametric cycle analysis method. The purpose of this study is to examine how engine performance is impacted by design parameters and flight ambient values and to develop a software in this context.</p><!--/ Abstract__block -->\\n<h3>Design/methodology/approach</h3>\\n<p>Software has been developed using the open-source PYTHON programming language to perform performance analysis. Mach number, compressor/fan pressure ratio, bypass ratio and density were used as parameters. The effects of these variables on engine performance parameters were investigated.</p><!--/ Abstract__block -->\\n<h3>Findings</h3>\\n<p>Parametric cycle analysis has been calculated for different flight conditions in the range of 0–2 M and 0–15,000 m altitude for turbofan engines. With this study, basic data were obtained to optimize according to targeted flight conditions.</p><!--/ Abstract__block -->\\n<h3>Practical implications</h3>\\n<p>As a result of the performance analysis, the association between the flight conditions and design parameters of engine were determined. A software has been developed that can be used in the design of supersonic gas turbine engines for fast and easy simulation of the design parameters.</p><!--/ Abstract__block -->\\n<h3>Originality/value</h3>\\n<p>The variables used in the literature have been analyzed, and the results of the studies have been incorporated into the developed software, which can be used in innovative engine design. Software is capable to be developed further with the integration of new algorithms and models.</p><!--/ Abstract__block -->\",\"PeriodicalId\":55540,\"journal\":{\"name\":\"Aircraft Engineering and Aerospace Technology\",\"volume\":\"40 1\",\"pages\":\"\"},\"PeriodicalIF\":1.2000,\"publicationDate\":\"2023-12-19\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Aircraft Engineering and Aerospace Technology\",\"FirstCategoryId\":\"5\",\"ListUrlMain\":\"https://doi.org/10.1108/aeat-01-2023-0021\",\"RegionNum\":4,\"RegionCategory\":\"工程技术\",\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q3\",\"JCRName\":\"ENGINEERING, AEROSPACE\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Aircraft Engineering and Aerospace Technology","FirstCategoryId":"5","ListUrlMain":"https://doi.org/10.1108/aeat-01-2023-0021","RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q3","JCRName":"ENGINEERING, AEROSPACE","Score":null,"Total":0}
Analysis of a turbofan engine using a parametric loop
Purpose
In this study, the performance analysis of the split flow turbofan engine with afterburners has been examined using the parametric cycle analysis method. The purpose of this study is to examine how engine performance is impacted by design parameters and flight ambient values and to develop a software in this context.
Design/methodology/approach
Software has been developed using the open-source PYTHON programming language to perform performance analysis. Mach number, compressor/fan pressure ratio, bypass ratio and density were used as parameters. The effects of these variables on engine performance parameters were investigated.
Findings
Parametric cycle analysis has been calculated for different flight conditions in the range of 0–2 M and 0–15,000 m altitude for turbofan engines. With this study, basic data were obtained to optimize according to targeted flight conditions.
Practical implications
As a result of the performance analysis, the association between the flight conditions and design parameters of engine were determined. A software has been developed that can be used in the design of supersonic gas turbine engines for fast and easy simulation of the design parameters.
Originality/value
The variables used in the literature have been analyzed, and the results of the studies have been incorporated into the developed software, which can be used in innovative engine design. Software is capable to be developed further with the integration of new algorithms and models.
期刊介绍：
Aircraft Engineering and Aerospace Technology provides a broad coverage of the materials and techniques employed in the aircraft and aerospace industry. Its international perspectives allow readers to keep up to date with current thinking and developments in critical areas such as coping with increasingly overcrowded airways, the development of new materials, recent breakthroughs in navigation technology - and more.
求助内容：
应助结果提醒方式：
京公网安备 11010802042870号
