a turbojet on a test stand air at inlet has density of 1.1 kg/m^3 at the exit gas has higher velocity and higher temp, but pressure is the same. inlet area is 0.5m^2 and free stream velocty is 200m/s. fuel air mix is 1:15 at exit, engine area is 0.3m^2, gas velocity 800m/s Determine the density of gas at exit and evaluate reaction forces to hold test stand

100% High pressure water and compressed air are delivered to some operating rooms. Bored one day, with no patients around, you take the cap off the nozzle to see what would happen. Water flows through the vertical pipe and nozzle and then exhausts into the air as shown in the diagram. The water pressure in the pipe at position 1 is 3 atm. The pressure when the water discharges to the air is 1 atm. Position 2 identifies the nozzle, 0.75 m above position 1, where the water flow has been constricted from an 8-cm diameter pipe to a 3-cm diameter nozzle. Assume that the free jet remains a stream of water with a 3-cm diameter. Assume no friction losses. Free jet -3 cm diameter 0.75 m a) Determine the mass flow rate of water through pipe at position 1 in kg/s. 3 atm 8 cm diameter b) Determine the height, h, the water jet can rise. c) Calculate the friction factor inside the 8-cm pipe and determine if the assumptions of negligible friction losses was reasonable. Water AR d 128 PM 10/3/2021…

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5. For the subsonic axial-flow air expander specified, calculate the stagnation and static pressures and temperatures and the Mach number at the rotor-inlet plane (figure P2.5). Also find the rotor rotational speed and the nozzle-inlet blade height for constant-outer-diameter blading. Sketch the form of the complete turbine expansion on an enthalpy-entropy chart. The axial velocity will be constant at this design point. Mass flow, m = 2 kg/s Nozzle-inlet stagnation temperature, Tuni = 400 °C. Absolute nozzle-inlet stagnation pressure, Po,ni = 3 bars(= 3 x 105 N/m²) Mean diameter, dm = 0.25 m. Blade height at rotor entry, 1 = 0.1dm(= 1/2[ds - dn]). Flow angle at nozzle exit, a₁ = 70° to axial direction. Drop in stagnation pressure in nozzle, Apo = 0.05 bar Rotor peripheral speed at mean diameter, um = 0.5x (component of nozzle outlet velocity, Ce,1).