Exam is Open Textbook, Open Class Notes, Computers can be used
(Computer limited to class notes, lectures, homework, book material, calculator,
conversion utilities, etc. No searching for similar problems at other sites.)
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To receive full credit all work must be clearly provided.
Please use units in all answers.
Problem 1: Air expands through a turbine operating at steady state on an instrumented
test stand. At the inlet, P1 = 160 lbf/in.2, T1 = 1560 °R, and at the exit, P2 = 14.8 lbf/in.2
The mass flow rate of air entering the turbine is 10.5 lb/s, and the power developed is
measured as 2580 horsepower. Neglecting heat transfer and kinetic and potential energy
effects, determine the exit temperature, T2, in °R.
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Problem 2: As shown below, air enters the diffuser of a jet engine operating at steady
state at P1 = 18 kPa, T1 = 216 K and a velocity of 265 m/s, all data corresponding to highaltitude flight. The air flows adiabatically through the diffuser and achieves a temperature
of T2 = 250 K at the diffuser exit (state 2). Using the ideal gas model for air, determine
the velocity of the air at the diffuser exit, in m/s (that is, immediately before entering the
compressor component of the jet engine.
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