Energy and performance optimization of an adaptive cycle engine for next generation combat aircraft

Basit Öğe Kaydı
dc.contributor.authorAygun, Hakan
dc.contributor.authorCilgin, Mehmet Emin
dc.contributor.authorEkmekci, Ismail
dc.contributor.authorTuran, Onder
dc.date.accessioned2021-01-25T21:47:57Z
dc.date.available2021-01-25T21:47:57Z
dc.date.issued2020
dc.departmentİstanbul Ticaret Üniversitesien_US
dc.descriptionekmekci, ismail/0000-0002-2247-2549;en_US
dc.descriptionWOS:000570077700012en_US
dc.description.abstractFor next generation aircraft, Adaptive Cycle Engine (ACE) is a candidate to fulfill the multi-mission requirements of flight. This new concept is promising to complete deficiencies of conventional low by-pass mixed turbofan engines because the ACE model incorporates different thermodynamic cycles (turbojet and turbofan) on the same air vehicle system. Firstly, performance and design results of the ACE model are compared with those of fixed cycle low by-pass turbofan engine by using specific fuel consumption (SFC), specific thrust (ST), power and efficiency parameters. Moreover, verification of the newly developed ACE model is performed. Secondly, considering some design parameters, ST and SFC values of the ACE model are analyzed for double by-pass mode (DBM) and single by-pass mode (SBM). Considering performance analysis of the ACE, SFC value is determined as 17.85 g/kN.s at DBM and 42.18 g/kN.s at SBM. According to results of energy analysis, overall efficiency of the ACE is calculated as 23% for DBM and 9% for SBM whereas fixed cycle engine has 18% for military mode and 7% for afterburner mode. Finally, minimization of (SFC) is obtained with genetic algorithm approach. Based on the design variables such as by-pass ratio and turbine inlet temperature, minimum SFC value for the ACE model is calculated as 17.41 g/kN.s at DBM and 40.45 g/kN.s at SBM. (C) 2020 Elsevier Ltd. All rights reserved.en_US
dc.description.sponsorshipEskisehir Tehnical University in Turkey; Eskisehir Tehnical University Scientific Research Projects Commission [20DRP056]en_US
dc.description.sponsorshipAuthors would like to thanks Eskisehir Tehnical University in Turkey for financial and technical support. This study was supported by Eskisehir Tehnical University Scientific Research Projects Commission under the grant no: 20DRP056.en_US
dc.identifier.doi10.1016/j.energy.2020.118261en_US
dc.identifier.issn0360-5442
dc.identifier.issn1873-6785
dc.identifier.scopus2-s2.0-85089155157en_US
dc.identifier.scopusqualityQ1en_US
dc.identifier.urihttps://doi.org/10.1016/j.energy.2020.118261
dc.identifier.urihttps://hdl.handle.net/11467/4466
dc.identifier.volume209en_US
dc.identifier.wosWOS:000570077700012en_US
dc.identifier.wosqualityQ1en_US
dc.indekslendigikaynakWeb of Scienceen_US
dc.indekslendigikaynakScopusen_US
dc.language.isoenen_US
dc.publisherPERGAMON-ELSEVIER SCIENCE LTDen_US
dc.relation.ispartofENERGYen_US
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanıen_US
dc.rightsinfo:eu-repo/semantics/openAccessen_US
dc.subjectAdaptive cycleen_US
dc.subjectEnergyen_US
dc.subjectTurbofanen_US
dc.subjectMilitary aircraften_US
dc.subjectOptimizationen_US
dc.titleEnergy and performance optimization of an adaptive cycle engine for next generation combat aircraften_US
dc.typeArticleen_US

Dosyalar

Orijinal paket
Listeleniyor 1 - 1 / 1
Küçük Resim Yok
İsim:
1-s2.0-S0360544220313682-main.pdf
Boyut:
4.1 MB
Biçim:
Adobe Portable Document Format
Açıklama:
İndir

Koleksiyon

WoS İndeksli Yayınlar Koleksiyonu
Scopus İndeksli Yayınlar Koleksiyonu