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Air at 22 kPa, 220K and 250 m/s enters a turbojet engine in flight at an altitude of 10,000m. The diffusor slows the air down to a very low speed relative to its inlet. The pressure ratio across the compressor is 12. The turbine inlet temperature is 1240 K, and the pressure at the nozzle exit is 22 kPa. The diffusor and nozzle processes are isentropic, the compressor and turbine have isentropic efficiencies of 85% and 88%, respectively, and there is no pressure drop for flow through the combustor. Using variable specific heats, determine:
A. The velocity at the nozzle exit in m/s.
B. Consider the addition of an afterburner to the turbojet engine that raises the temperature at the inlet of the nozzle to 1100K. Determine the new velocity at the nozzle exit.
a 25 degree full-depth spur gear with 45 teeth has an addendum of 13 in. what is the minimum number of teeth the pinion
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Determine the force in member BC. After the truss is sectioned use a single equation of equilibrium for the calculation of each force. State if these member is in tension or compression. Take F1 = 2 kN , F2 = F3 = 3.8kN , F4 = 5 kN, F5 = 3 kN.
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