Problem 4: Consider the following schematic of a simple turbojet engine model that uses air as its working fluid. With the data given determine (A) the pressure and temperature of all five states, (B) the amount of heat added in the burner, (C) the necessary air-to-fuel ratio of the engine, (D) the amount of power required by the compressor, and (E) the velocity of the exhaust stream at the exit of the system. Note: The variable rp is the compressor ratio defined to be the pressure of the compressor exit to the pressure of the compressor inlet. Assume that the compressor, turbine, and nozzle are all adiabatic and reversible. The Turbo jet Engine 2 R = P; : 100 kfa %3D 3 Burner T,: 300 k 6: 12 5: 1200 K Kefpo 4/3 %3D FHV = 43 KJ/g-fred

1. A hole in the bottom of a large open tank discharges water to the atmosphere. If the exit velocity in the absence of losses is Ve, find the loss coefficient for the hole if the actual velocity is Ve/2. Assume turbulent flow. 2. Air enters a duct at a speed of 100 m/s and leaves it at 200 m/s. If no heat is added to the air and no work is done by the air, what is the change in temperature of the air as it passes through the duct?  

please show how to derive h using nusselt equation and solve for qheatloss

Determine the efficiency for the cycle (standard air used as the working fluid) indicated in the sketch. Assume the pressures and temperatures are known quantities at each state. 1-2 constant volume process and 2-3 constant pressure process.

Separate streams of air and water flow through the compressor and heat exchanger arrangement shown below. Steady-state operating data is provided in the figure. Heat transfer with the environment can be neglected, as can all potential and kinetic energy effects. Air is modeled as an ideal gas. Determine: (a) the total power required by both compressors, in kW. (b) the mass flow rate of the water, in kg / s.

Q.3 A converging-diverging nozzle is supplied by a huge air reservoir. The nozzle has a throat area of 10 cm? and an exit area of 20 cm?. The reservoir conditions are P. = 300 kPa and To = 30 °C. Determine the range of the back pressure over which (a) shocks appear in the nozzle, (b) oblique shocks form at the exit, and (c) expansion waves form. (d) Calculate the mass flow rate through the nozzle for the case in which a normal shock appears at the exit plane.

A gas turbine power plant with the following specifications: two axial compressor stages, the pressure ratio is 6/1 for each compressor. The inlet and exit angles of both moving and fixed blades are 40° and 20° respectively, the work done factor is 0.82, six stages for each compressor. intercooling between stages. A high pressure turbine is used to drive the compressors, and a low pressure turbine drives the generator. The temperature of the gases at entry to the high pressure turbine is 600°C and the gases are reheated to 700°C after expansion in the first turbine. The exhaust gases leaving the low pressure turbine are passed through a heat exchanger to heat the air leaving the high pressure stage compressor. The air inlet temperature to the unit is 20°C. The isentropic efficiency of each turbine stage is 0.95; the heat exchanger thermal ratio is 0.7. A mechanical loss is 5% for both the generator- turbine shaft and the compressor- turbine shaft. Assume any missed values to Calculate…