Details

Autor(en) / Beteiligte

• Siddhartha, D. V. S.
• Jayakumar, J. S.

Titel

Numerical Investigation on Effect of Density Ratio of Effusion Cooled Combustor Liner Flat Plate

Ist Teil von

• Advances in Fluid and Thermal Engineering, 2023, p.405-415

Ort / Verlag

Singapore: Springer

Erscheinungsjahr

2023

Link zum Volltext

Quelle

Alma/SFX Local Collection

Beschreibungen/Notizen

• Effusion cooling represents the state-of-the-art cooling methodology for liners in modern gas turbine engine combustors. Advanced combustion techniques in aero engines require highly effective effusion cooling schemes for the combustor liner to protect it from extremely hot gases by consuming a minimum amount of air for cooling. The primary intention behind the present study is to find the best cooling performance for a particular phase of flight. The phase of flight considered are idle (DR = 1.2), takeoff (DR = 5) and cruise (DR =  5). The combustor liner is modeled as a flat plate with 72 coolant holes with the hole diameter d = 2 mm, with three different inclination angles α =20°, 30°, 40° and along the streamwise direction the pitch to diameter ratio of 4 is chosen. The mainstream conditions are maintained with the inlet velocity of 24 m/s, the temperatures as 361 k, 750 k and 1500 k. The coolant to mainstream blowing ratios are maintained at 1, 2 and 3, and the coolant temperature is 300 k. Area averaged cooling effectiveness is obtained by using CFD simulation using ANSYS® Fluent solver and the flow field is solved by using k-ϵ with an enhanced wall treatment turbulence model. The numerical results are validated with the experimental values available in the literature. The area averaged results showed that for a phase of flight the cooling effectiveness increases with an increased blowing ratio. The coolant film thickness increases as the blowing ratio is increased. The shallow coolant injection angle provided better cooling effectiveness.