Example 26.13 An axial-flow compressor draws air at 20°C and delivers it at 50°C. Assuming 50% reaction, calculate the velocity of flow, if blade velocity is 100 m/s, work factor is 0.85. Take C₂ = 1 kJ/kg K, Assume Cp 10°, and B = 40°. Find the number of stages. a =

Problem-5: In a CD nozzle with a throat area of 0.75 m² of a rocket engine, gas at 7.5 MPa and temperature of 3200 K is in combustion chamber, is expanded fully to (nozzle exit pressure) 10.5 kPa for producing thrust. Assuming flow to be frozen and isentropic, Also, Assume, gamma, y 1.2 and molecular weight, MW = 24 kg/kmol, Assume, universal gas = constant = 8314 J/Kg K mol Determine: (1) the exit Mach number, (2) the maximum exit mass flow rate passing through this nozzle, and (3) the exit area (4) If ambient pressure, i.e. pressure outside nozzle = 10.5 kPa, What is the thrust developed? Fuel Oxidant Combustion zone Mixture of Hot gas at high pressure and Temprature Expansion Through Nozzle High velocity exhaust Liquid Propellant Rocket

Please don't provide handwritten solution ......

A The compression ratio of a diesel cycle is 15.5, and the cutoff occurs at 10% of the stroke. 14 psia and 600 K characterize state 1. Calculate the following for the hot-air standard with k= 1.34 and a starting volume of 2 cu ft: Qin a. Find T2 , P2 , V2 , T3 , V3 , P4 , and T4 3 P = P, b. Compute the heat added (QA), Wout heat rejected (Qr), work (W) and the cycle efficiency (e). P. c. for a rate of circulation of 1000 cfm, Qout compute the horsepower.