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 =

4.1 A gas turbine power plant is operating as follows. Compressor intake air temperature T, is 306 K, pressure p, is 100 kPa, and compressor pressure ratio B is 15. TIT T, is 1490 K. Isentropic efficiency of compressor N, is 0.88, and that of turbine n is 0.91. Air mass flow rate mi, is 636 kg/s. Fuel mass may be ignored. Calculate (i) actual temperatures at compressor and turbine exits, (ii) plant actual net specific work per kg air, (iii) plant actual power output, (iv) plant actual rates of heat addition and rejection, and (v) plant actual thermal efficiency.

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 ......

9.2 The inlet stagnation temperature of a centrifugal compressor rotating at 10,000 rpm is 20°C. The inlet flow is axial and the blades are radially tipped at the exit. It is required to produce a stagnation pressure ratio of 2.8 when the total to total effi- ciency is 0.85. It has 19 blades and a mass flow rate of 3.0 kg/s. Through measure- ments, the density of air at the exit of the impeller is found to be 1.5 kg/m³. The width of the blades at the exit is 1 cm. Calculate the following: (a) power required to drive the compressor, (b) diameter of the impeller, and (c) absolute Mach num- ber at the exit. Use Stanitz's equation for the slip coefficient. Ans: 355 kW; 0.694 m; 0.897

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= 1.34and a starting volume of 2 cu ft:a. Find T2 , P2 , V2 , T3 , V3 , P4 , and T4b. Compute the heat added (QA),heat rejected (QR), work (W) andthe cycle efficiency (e).c. for a rate of circulation of 1000 cfm,compute the horsepower.

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:a. Find T2 , P2 , V2 , T3 , V3 , P4 , and T4b. Compute the heat added (QA), heat rejected (QR), work (W) and the cycle efficiency (e).c. for a rate of circulation of 1000 cfm, compute the horsepower

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.

Steam enters a control yolume that has one inlet and two exits. At the inlet (location 1) with a diámeterof 5.2 cm, the Steam has 100 bar , 360°C , and as mass flow rate of a Rg/sec. Through one exit (location 2), 15.% of the incoming mass flow rate Teaves the Control volume and the remainder leaves through the otner exit (locatión 3). For steady state opeaton, calculake the mass flow rate at locatlon 3 in kg/sec using 5 Signifigant figiures. रप्री द

The last 3 parts B,D,E