چكيده به لاتين
Gas turbines are used to propel airplanes and generators of ground power and other industrial applications. The thermal efficiency and power output of the gas turbine increase with increasing the Temperature of gas turbine input. Due to the temperature limitation of alloys used in the manufacture of gas turbines, it is necessary to reduce the temperature of turbine components, especially turbine blades. Cooling of turbine blades is performed internally and externally. In internal cooling, the coolant flow through the blades reduces their temperature. Due to the nature of the turbine gas, the flow of fluid through the cooling channel is influenced by the Coriolis force and the centrifugal along with the buoyancy force induced by heat transfer. On the other hand, due to the nature of the turbine blades, the cooling channels are angled relative to the axis of the rotation a test Setup is being developed in this Research to verify the validity of these Correlation. The main test channel consists of a square-channel channel, which Turbolator elements on its lateral walls. The heat flux is applied by using a number of heaters on the side walls, and on the other hand by Streaming the flow of the cooling fluid in this channel, these walls are cooled. This Setup can test in the Reynolds range from 5,000 to 120,000 and in the Rotaion Number range of 0 to 0.5. the non-angular state of the channel Nusselt number decrease 5% at the leading edge, and increase at the trailing edge by 20%, and the average Nusselt number increases. In the case of 45 and a rotation number of 0.1 on the leading edge,% 2 increases, and on the trailing edge is 8% of the increase in the Nusselt number, at -45, the Nusselt number increases on the leading edge by 5% and on the trailing edge ,% 2 Decreases. According to the actual conditions of operation of gas turbine blade and the use of modern cooling techniques, the highest cooling rate with the lowest thermal stress in turbine gas blades can be achieved.
