Naslov
The influence of film cooling flow over turbine blades from different shaped holes

Autori
Cerinski, Damijan ; Baleta, Jakov ; Wang, Jin ; Wang, Xuebin

Vrsta, podvrsta i kategorija rada
Radovi u zbornicima skupova, cjeloviti rad (in extenso), znanstveni

Izvornik
Proceedings of the European Combustion Meeting 2019 / Costa, Mário ; Pereira, Sandrina - Lisabon : Instituto Superior Técnico, 2019

Skup
9th European Combustion Meeting (ECM 2019)

Mjesto i datum
Lisabon, Portugal, 14.04.2019. - 17.04.2019

Vrsta sudjelovanja
Poster

Vrsta recenzije
Nije recenziran

Ključne riječi
CFD ; turbine blades ; film cooling

Sažetak
The influence of different shaped holes on the film cooling performance of gas turbine blades was numerically investigated. The hot stream of exhaust gasses from the combustion chamber enters the turbine section of gas turbine engines at high velocity and temperature. The combustion efficiency highly depends on the temperature, but currently used turbine blades materials are not capable to withstand such conditions, therefore utilising the film cooling system is necessary. In this work, CFD simulations were performed to describe the interaction between the hot stream gas from the combustion chamber and the coolant jet from a shaped hole. The computational domain consisted of a hot gas channel and a cooling shaped hole. The validation case with the cylindrical hole was compared to the experimental results and results from LES simulations available in the literature. Temperature distributions were analysed and compared to the case with a cylindrical hole to investigate the influence of different shaped holes on cooling performance. The results showed the possibility of improving the film cooling performance through different design of cooling holes which allows the increase of the temperature in the combustion chamber, and consequently overall combustion efficiency.

Izvorni jezik
Engleski

Znanstvena područja
Metalurgija, Strojarstvo, Zrakoplovstvo, raketna i svemirska tehnika

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