Engineering, 26.02.2020 03:58 musicalmel
Consider an ideal turbojet with an afterburner operating at flight Mach number of 2.0 at an altitude where the ambient static temperature: Ta = −70 ◦C and static pressure: pa = 15 kPa. The compressor pressure ratio is 10, the maximum temperature at the entrance to the nozzle is 2250 ◦K while the turbine outlet temperature is 700 ◦K. We assume that the exit Mach number Megxit = Mf light with the flow expanding in the nozzle to the ambient conditions at the exit. If the total fuel-to-air ratio for = 0.0519 for a fuel heating value of 45,000 kJ/kg, then determine:
Answers: 2
Engineering, 04.07.2019 18:10
Shafts are machine elements that are used to a) carry axial loads b) direct shear loads c) transmit power d) rotate at constant speed e) none of the above circular and square shafts subjected to the same torque under the same circum behave a) the same way b) almost the same way
Answers: 2
Engineering, 04.07.2019 18:10
Machinery that is a key part of the process and without which the plant or process cannot function is classifed as: (clo4) a)-critical machinery b)-essential machinery c)-general purpose machinery d)-none of the specified options.
Answers: 1
Engineering, 04.07.2019 18:20
Determine the damped natural frequencies and the steady state response of a decoupled damped forced two degrees of freedom system. 10ä1 + 2q1 20q1 10 cos t; 10q2 +4q2 + 40q2 10 cos t
Answers: 3
Engineering, 04.07.2019 19:10
Asteam is contained in a rigid tank with a volume of 1 m3. initially, the pressure and temperature are 7 bar and 500 oc, respectively. the temperature drops due to cooling process. determine: (1) the temperature at which condensation begins in °c, (2) the fraction of the total mass that has condensed when the pressure decreased to 0.5 bar. (3) the volume in m3 occupied by saturated liquid at the final state?
Answers: 3
Consider an ideal turbojet with an afterburner operating at flight Mach number of 2.0 at an altitude...
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