Consider a turbojet engine (no-afterburner) cruising at M=0.85, at 40,000 ft (Pa = 18.75kPa and Ta=217K), with fixed m
Posted: Wed Apr 27, 2022 8:27 pm
Consider a turbojet engine (no-afterburner) cruising at M=0.85, at 40,000 ft (Pa =
18.75kPa and Ta=217K), with fixed maximum temperature T04=1600K. Why does the
specific thrust emerge as a non-monotonic function (increases and then decreases) of
the compressor pressure ratio? Explain with analysis and brief thermodynamic
arguments. Assume relevant adiabatic efficiencies, if required.
18.75kPa and Ta=217K), with fixed maximum temperature T04=1600K. Why does the
specific thrust emerge as a non-monotonic function (increases and then decreases) of
the compressor pressure ratio? Explain with analysis and brief thermodynamic
arguments. Assume relevant adiabatic efficiencies, if required.