Mathematical Model and Calculation of Heat Transfer Coefficients of Rough Turbulent-Flow-Carrying Channels

Technical solutions for increasing efficiency of gas turbine engines

“…Determining the extent of areas on the blade profile with laminar, transitional and turbulent flow, it is important to determine flow patterns and heat transfer in each region, which determine the distribution along the blade profile of local heat transfer coefficients from the gas to the blade surface. The gas turbine engines with moderate Reynolds number of initial temperature of the gas turbine blades are typically 10 5 …10 6 . In high-temperature gas turbine engines, the Reynolds numbers reach 9•10 6 .…”

“…The gas turbine engines with moderate Reynolds number of initial temperature of the gas turbine blades are typically 10 5 …10 6 . In high-temperature gas turbine engines, the Reynolds numbers reach 9•10 6 . The average value of the perimeter of the profile of the heat transfer coefficient on the gas side is 200 -1200 W/(m 2 •degrees), and in the hightemperature gas turbine engine -up to 5000 W/(m 2 •degrees).…”

“…To determine the friction and the distribution of coolant flow can be used for calculating the approximate engineering method. Numerous experiments have shown that the stabilized developed turbulent fluid flow in channels of different shapes depending on the nature of the frictional resistance coefficient Reynolds number is the same as in the flow in the cylindrical channel [6,8].…”