Analysis of a turbofan engine using a parametric loop.
Saved in:
| Title: | Analysis of a turbofan engine using a parametric loop. |
|---|---|
| Authors: | Dişlitaş, Ayşe Nur1 (AUTHOR) aysenurdislitas@erciyes.edu.tr, Albayrak Çeper, Bilge2 (AUTHOR) balbayrak@erciyes.edu.tr, Yıldız, Melih1 (AUTHOR) melihy@erciyes.edu.tr |
| Source: | Aircraft Engineering & Aerospace Technology. 2024, Vol. 96 Issue 1, p121-128. 8p. |
| Subjects: | Turbofan engines, Python programming language, Mach number, Internal combustion engines, Gas turbines |
| Abstract: | 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. [ABSTRACT FROM AUTHOR] |
| Copyright of Aircraft Engineering & Aerospace Technology is the property of Emerald Publishing Limited and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract. (Copyright applies to all Abstracts.) | |
| Database: | Engineering Source |
| FullText | Text: Availability: 0 |
|---|---|
| Header | DbId: egs DbLabel: Engineering Source An: 175262586 AccessLevel: 6 PubType: Academic Journal PubTypeId: academicJournal PreciseRelevancyScore: 0 |
| IllustrationInfo | |
| Items | – Name: Title Label: Title Group: Ti Data: Analysis of a turbofan engine using a parametric loop. – Name: Author Label: Authors Group: Au Data: <searchLink fieldCode="AR" term="%22Dişlitaş%2C+Ayşe+Nur%22">Dişlitaş, Ayşe Nur</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> aysenurdislitas@erciyes.edu.tr</i><br /><searchLink fieldCode="AR" term="%22Albayrak+Çeper%2C+Bilge%22">Albayrak Çeper, Bilge</searchLink><relatesTo>2</relatesTo> (AUTHOR)<i> balbayrak@erciyes.edu.tr</i><br /><searchLink fieldCode="AR" term="%22Yıldız%2C+Melih%22">Yıldız, Melih</searchLink><relatesTo>1</relatesTo> (AUTHOR)<i> melihy@erciyes.edu.tr</i> – Name: TitleSource Label: Source Group: Src Data: <searchLink fieldCode="JN" term="%22Aircraft+Engineering+%26+Aerospace+Technology%22">Aircraft Engineering & Aerospace Technology</searchLink>. 2024, Vol. 96 Issue 1, p121-128. 8p. – Name: Subject Label: Subjects Group: Su Data: <searchLink fieldCode="DE" term="%22Turbofan+engines%22">Turbofan engines</searchLink><br /><searchLink fieldCode="DE" term="%22Python+programming+language%22">Python programming language</searchLink><br /><searchLink fieldCode="DE" term="%22Mach+number%22">Mach number</searchLink><br /><searchLink fieldCode="DE" term="%22Internal+combustion+engines%22">Internal combustion engines</searchLink><br /><searchLink fieldCode="DE" term="%22Gas+turbines%22">Gas turbines</searchLink> – Name: Abstract Label: Abstract Group: Ab Data: 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. [ABSTRACT FROM AUTHOR] – Name: AbstractSuppliedCopyright Label: Group: Ab Data: <i>Copyright of Aircraft Engineering & Aerospace Technology is the property of Emerald Publishing Limited and its content may not be copied or emailed to multiple sites without the copyright holder's express written permission. Additionally, content may not be used with any artificial intelligence tools or machine learning technologies. However, users may print, download, or email articles for individual use. This abstract may be abridged. No warranty is given about the accuracy of the copy. Users should refer to the original published version of the material for the full abstract.</i> (Copyright applies to all Abstracts.) |
| PLink | https://search.ebscohost.com/login.aspx?direct=true&site=eds-live&db=egs&AN=175262586 |
| RecordInfo | BibRecord: BibEntity: Identifiers: – Type: doi Value: 10.1108/AEAT-01-2023-0021 Languages: – Code: eng Text: English PhysicalDescription: Pagination: PageCount: 8 StartPage: 121 Subjects: – SubjectFull: Turbofan engines Type: general – SubjectFull: Python programming language Type: general – SubjectFull: Mach number Type: general – SubjectFull: Internal combustion engines Type: general – SubjectFull: Gas turbines Type: general Titles: – TitleFull: Analysis of a turbofan engine using a parametric loop. Type: main BibRelationships: HasContributorRelationships: – PersonEntity: Name: NameFull: Dişlitaş, Ayşe Nur – PersonEntity: Name: NameFull: Albayrak Çeper, Bilge – PersonEntity: Name: NameFull: Yıldız, Melih IsPartOfRelationships: – BibEntity: Dates: – D: 01 M: 01 Text: 2024 Type: published Y: 2024 Identifiers: – Type: issn-print Value: 17488842 Numbering: – Type: volume Value: 96 – Type: issue Value: 1 Titles: – TitleFull: Aircraft Engineering & Aerospace Technology Type: main |
| ResultId | 1 |
