Question

compare the maximum work delivered by an aircraft gas turbine which works in following two atmospheric condition.(two stage compressor with perfect inter-cooler, but without reheat and regeneration). compressor pressure ratio is 4 and metallurgical temperature limit is 1000k. At ambient condition : pressure = 1 bar and temperature = 301 k
At 6000 m altitude pressure= 0.5 bar and temperature=248k.
Find percentage change in net work output, efficiency.