Naslov
Numerical study of effusion cooling of a gas turbine combustor liner

Autori
Wang, Jin ; Hu, Zhenwei ; Du, Cong ; Tian, Liang ; Baleta, Jakov

Izvornik
Fuel (Guildford) (0016-2361) 294 (2021); 120578, 10

Vrsta, podvrsta i kategorija rada
Radovi u časopisima, članak, znanstveni

Ključne riječi
Effusion cooling ; Combustor ; Cooling performance ; Inclination angle ; Film cooling

Sažetak
Effusion cooling is known as one of the most effective methods to provide cooling protection for hightemperature components in gas turbines. It is widely used in combustion chamber liner cooling. In this paper, different inclination angles of cooling holes were considered to investigate an effect of effusion cooling in a combustion chamber liner. The present work carried out numerical simulations based on a Can - type gas turbine combustor, and propane was used as fuel. Reynolds stress model (RSM) was used for turbulence and the steady diffusion flamelet of non-premixed combustion. The numerical model was respectively validated under isothermal and combustion conditions. Results show that the effusion cooling provides good protection for the combustor liner, which contributes to a maximum temperature reduction of 31.7%. It is found that the best cooling effectiveness effect is obtained when the hole inclination angle is 30◦, which is 10.4% higher than that with 90◦ inclination angle. A uniform outlet temperature distribution is significantly important to protect for turbine blades. The pattern factor is 1.33, 1.35 and 1.36 for cases with 30◦, 60◦ and 90◦ inclination angles of cooling holes. The smaller value of the pattern factor represents more uniform temperature distribution. According to the pattern factor, the temperature distribution is most uniform when the inclination angle is 30◦. This result for the 30◦ inclination angle corresponds to an increase of 2.2% compared to that for the 90◦ inclination angle.

Izvorni jezik
Engleski

Znanstvena područja
Metalurgija, Strojarstvo

POVEZANOST RADA