Mohamad Reza Nazari - Department of Mechanical and Aerospace Engineering, Malek Ashtar University of Technology, shiraz, Iran
Behrooz Shahriari - Department of Mechanical and Aerospace Engineering, Malek Ashtar University of Technology, ۸۴۱۴۵-۱۱۵, Isfahan, Iran.
Farhad Sebghatollahi - Department of Mechanical and Aerospace Engineering, Malek Ashtar University of Technology, ۸۴۱۴۵-۱۱۵, Isfahan, Iran.

Increasing the temperature of the turbine entrance gases increases the efficiency of the gas turbine cycle. Under these conditions, the combustion chamber wall temperature also increases, while there is no high temperature resistance alloy fitted with air motors. Therefore, it is necessary to use cooling methods to reduce the wall temperature. In this study, the cooling effect with compound angles investigated on the combustion chamber wall temperature. The three-dimensional combustion chamber k-ɛ is modelled under the conditions of the input speed and the turbulence model in the ANSYS Fluent software. Inlet air is injected from the cooled holes to the mainstream with compound angle, where the cooling flow angle is constant with the ۳۰° horizontally, and the lateral angle changes from Beta =۰ up to Beta=۶۰ degrees. The combustion chamber has two flat planes and two sloping plates, in which the arrangement of cooling holes is different. The results show that this method better distributes the cooling air on the wall surface and covers the space between the cooling holes, especially on flat plates. With this method, the number of cooling holes and the amount of air used to cooling can be reduced. 

Combustion Chamber, Compound Angle, Film Cooling, Wall Temperature