hi guys. new to the forum. im a mechanical engineer by trade, but have been asked by by my nephew now studing engineering a turbofan question and need a little nudge in the right direction
His question reads
An aircraft powered by turbofan engines cruises at a Mach No. of 0.82, at an altitude where Ta = 223.3K and Pa = 0.265 bar. Each engine has a by-pass ratio of 4.8 and a total mass flow rate of 210 kg/s at these conditions. The fan pressure ratio is 1.75 and the fan efficiency is 97%. The intake efficiency is 94% and the by-pass nozzle efficiency is 100%.
Calculate the thrust from one of the engines produced by the by-pass air alone.
now i understand that the thrust is going to be a combination of the bypass and the main core thrust.I can get the compressor work but the problem which i am having is figuring the turbine entry temperature.
can any of you pros out there assist
much appreciated
