Cooling effectiveness and aerodynamic performance in a 2D-Contoured endwall passage with different mass flow ratios

Chen, Pingting; Alqefl, Mahmood H.; Li, Xueying; Ren, Jing; Jiang, Hongde; Simon, Terrence W.

doi:10.1016/j.ijthermalsci.2019.04.031

Cited by 18 publications

(1 citation statement)

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“…Several numerical and experimental works have been done to analyze the influence of film cooling on gas turbine performance. Nowadays, the CFD prediction of the film cooling method is a valuable part of designing the process of the cooling scheme for gas turbines [21,22]. The infrared thermography was utilized in the study of Kim et al [23] to analyze the impact of different injection holes over a gas turbine blade for film cooling.…”

Section: Introductionmentioning

confidence: 99%

Film cooling modeling of a gas turbine blade by considering different injection holes with and without opening angles through CFD

Hosseini¹

2021

JMES

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One way to achieve high performance in the gas turbine is to increase the inlet temperature of the turbine. Different cooling techniques have been carried out in order to protect the turbine blades which have been exposed to such high temperatures. Film cooling as an essential cooling method needs to be enhanced to meet the challenging demand. The purpose of the present research is to analyze the film cooling performance over a NACA 0012 gas turbine blade using six different injection holes with and without opening angles, separately through Computational Fluid Dynamics (CFD). 2D Reynolds-Averaged Navier-Stokes (RANS) equations are implemented to consider the heat transfer and flow characteristics by using CFD code Ansys Fluent v16. The flow is considered as steady, turbulent, and incompressible. The RANS equation is solved with the finite-volume method for obtaining solutions. The simulation results revealed that the k-ω SST turbulence model is suitable for simulating the flow characteristics and analyzing the performance of film cooling over the blade. Also, the opening angle has a significant effect on increasing the cooling efficiency for the upper blade surface. The highest value of cooling efficiency is obtained by the injection hole with an opening angle of 15° and height of D. In this configuration, the coolant injected from hole provides better cooling coverage for the entire blade which increases the cooling effectiveness.

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Section: Introductionmentioning

confidence: 99%