Abstract
The cooling effectiveness of combustor transition pieces increases significantly in accordance with turbine temperature. In this issue, we create a scenario in which using three-dimensional computational to predict the performance of film cooling model with three rows holes and double chambers on the flat surface that the model could simulate the TPâ??s structure and performance. Fluent, a commercial CFD software, is extensively used in the current work for numerical simulations. A comprehensive study is performed on the effect of coolant injection angles on film cooling. The the temperature distribution in the inner wall, cooling effectiveness, and the velocity distribution of coolant flow with different cases is compared. Analysis on flow injection orientations is beneficial to enhance the turbine inlet temperature and improve gas turbine efficiency
Highlights
A major challenge associated with gas turbine design is developing methods to cool combustor components so that higher gas temperatures and better performance can be achieved
It is seen from the figure that the effectiveness is maximum between the X=480 mm and 620 mm of the inner wall, which part is under the film region of the outer wall
Film cooling effectiveness increases with injection angle, which is because more cooling air is directly reached the inner wall surface and provides better cooling
Summary
A major challenge associated with gas turbine design is developing methods to cool combustor components so that higher gas temperatures and better performance can be achieved. Many experimental and computational studied have been conducted in order to study the cooling process of gas turbine blades [1], understand this complex flow and heat process, and devise the best possible cooling schemes. This operating temperature is far above the permissible temperature of currently available thermal-resistive materials. A cooling technique has to be established to prevent the thermal degradation of turbine components
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