HEAT TRANSFER ANALYSIS IN THE TBC COATED EXHAUST NOZZLE OF GAS TURBINES

ALTUN Ö.

HEAT TRANSFER RESEARCH, cilt.46, sa.1, ss.13-29, 2015 (SCI-Expanded) identifier identifier

  • Yayın Türü: Makale / Tam Makale
  • Cilt numarası: 46 Sayı: 1
  • Basım Tarihi: 2015
  • Doi Numarası: 10.1615/heattransres.2014005781
  • Dergi Adı: HEAT TRANSFER RESEARCH
  • Derginin Tarandığı İndeksler: Science Citation Index Expanded (SCI-EXPANDED), Scopus
  • Sayfa Sayıları: ss.13-29
  • Eskişehir Osmangazi Üniversitesi Adresli: Evet

Özet

Estimation of temperature distribution in hot section components plays an important role in the development of new generation of gas turbines. In this study, temperature distribution in a thermal barrier coated exhaust nozzle has been investigated. The numerical simulations were carried out using commercial codes FLUENT and GAMBIT to calculate heat transfer distributions. The temperature distributions in the exhaust nozzle were calculated taking into consideration all three heat transfer mechanisms: conduction, convection, and radiation. The wall temperature is significantly decreased by thermal barrier coating.