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- Air at a tempenature of 27°C floves into a centrifugal compressor at 20000 pm. The following data are given: Slip factor 080 Power input factor 1 Isentroric efficiency 80% Outer diameter of blade tin 0.5 m Assuming the abslute velocities of air entering and leaving the compressor are same, find i) static temperature nise of air passing thnough the compesson, and 'ii) the static pressure ratio. p c of air is 1005 F/ kgkWrite the components of Sub-Sonic Wind Tunnel?A simple jet carburetor is required to supply 5 kg of ai and 0.5 kg of fuel per minute. The fuel specific gravity is 0.75. Thrnea'r is initially at 1 bar and 300 K. Calculate the throat diameter or ir choke for a flc ty ocity of 100 m/s. Velocite oefficient is 0.8. If the pressure drop acit 1 1he fuel metering orific orifice diameter assuming. Caf .60 and= 1.4. 80 of that of the choke. calculate
- Assuming the clearance is negligible for a single stage compressor with the following data.Atmospheric pressure: 90 kPaAtmospheric temperature: 17 ˚CDelivery pressure: 7 barFree air delivery flow rate: 0.2 m3/minTake “n” as 1.3, cp = 1.005 kJ/kg K, cv = 0.718 kJ/kg K 1.What is the power input to the compressor in kW to 3 decimal places if the compression reversible isothermal?Assuming the clearance is negligible for a single stage compressor with the following data.Atmospheric pressure: 90 kPaAtmospheric temperature: 17 ˚CDelivery pressure: 7 barFree air delivery flow rate: 0.2 m3/minTake “n” as 1.3, cp = 1.005 kJ/kg K, cv = 0.718 kJ/kg K 1.What is the power input to the compressor in kW to 2 decimal places if the compression is polytropic compression process with n=1.25?Assuming the clearance is negligible for a single stage compressor with the followingdata.Atmospheric pressure: 90 kPaAtmospheric temperature: 17 ˚CDelivery pressure: 7 barFree air delivery flow rate: 0.2 m3/minTake “n” as 1.3, cp = 1.005 kJ/kg K, cv = 0.718 kJ/kg K 1. What is the power input to the compressor if compression is isentropic in kW to 3 decimal places? 2. What is the power input to the compressor in kW to 3 decimal places if the compression reversible isothermal?
- (1) A four-cylinder, two-stroke cycle diesel engine with 10.9 cm bore and 12.6 cm stroke produces 88 kW of brake power at 2000 r.p.m. compression ratio rc-18:1. calculate :- (a) engine displacement. (cm³,L) (b) brake mean effective pressure. (kpa) (c) torque. (N.m) (d) clearance volume of one cylinder. (cm³) ANS: (a) 4703,4.703, (b) 561, (c) 420, (d) 69.2O An inward flow reaction furbine develops 130 kw under a head Bm. Thhe flow Velocity is 4m/s and The runner fangentiaf Velocity at in let is 9.6m/s. The runner rotater at 230rem while hydraulie Cosses aclounting for 20% of The energy available.find: 1- Plot The Velocity diagram . 2- The inlet auide Vane angle. 3- The inlet ana le to The runner Vane. 4 -The runner diameta at The inlet. 5-The width of The runner atinlet. A ssum vadiaf discharge and overall efficiency equal to 72%. .For solution of this problem also sketch velocity triangles and label it. A rotodynamic impulse turbine was used to develop power. In an impulse stage the mean diameter of the blade ring is 900 mm and the speed of rotation is 3500 1.p.m The nozzle angle is 22º and the steam exits from the nozzles with a velocity of 350 m / s. Assuming the blade velocity coefficient as 0.85 and also suppose that the blades are symmetric When the axial thrust on the blades is 150 N. Determine the power developed.
- Assuming the clearance is negligible for a single stage compressor with the followingdata.Atmospheric pressure: 90 kPaAtmospheric temperature: 17 ˚CDelivery pressure: 7 barFree air delivery flow rate: 0.2 m3/minTake “n” as 1.3, cp = 1.005 kJ/kg K, cv = 0.718 kJ/kg K Calculatate the following 1 )Evaluate the mass flow rate of air inside the compressor operating isentropically in kg/min to 3 decimal places. 2 ) What is the power input to the compressor in kW to 3 decimal places if the compression reversible isothermal? 3 ) What is the power input to the compressor in kW to 2 decimal places if the compression is polytropic compression process with n=1.25?a) A convergent nozzle with a given area ratio is supplied with air at a constant stagnation pressure Poand a constant stagnation temperature To. With the aid of a sketch plot the nozzle mass flow rate as a function of pressure ratio () across P the nozzle. In your answer indicate the critical value of the pressure ratio. For air you may assume y = 1.4 and R = 287J/kg K. b) The engine of a supersonic aircraft is equipped with a convergent-divergent nozzle. A A, A -4.0).Determine the design subsonic and supersonic Mach numbers for this area ratio. You may assume the combustion products have the same properties as air and the expansion process through the nozzle is isentropic. The nozzle's area ratio is ( c) Determine at what pressure ratios ( ) a normal shock wave appears in the P divergent part of the nozzle at a location where -3.0) Aheck A₁Air flows through a cylindrical combustion chamber of diameter 0.3 m and length 3 m as shown in the figure below. M₁ T₁ P₁ 1 L 2 M₂ T₂ P₂ Stations (1) and (2) are the inlet and outlet, respectively. The inlet stagnation temperature is 1,000 K and the inlet stagnation pressure is 1.5 MPa. = a) If the skin friction coefficient is Cf 0.004 (approximately uniform) and no combustion takes place, what will be the inlet Mach number if it is subsonic and the exit Mach number is unity? What are the values of static and stagnation pressure at the exit? b) If combustion takes place and the heat of reaction is 600 kJ/kg of mixture, neglecting frictional effects, and if the inlet Mach number is 0.25, what is the exit Mach number? What are the values of static and stagnation pressure at the exit? The combustion process may be simulated by simple heating with constant specific heat ratio. The fluid may be considered a perfect gas with y = = 1.4 and a molecular weight of 29 kg/kmol.