An axial flow Impulse gas turbine stage receives a mass flow rate of 76 lbm/s at a velocity V1. It has a hub and tip radii of 7 in and 12 in respectively. The gas leaves the stator with an angle of a;=45° with the tangential direction. The blade angle at the outlet is Bp2=36.07°. Take pgas=0.085 lbm/ft. a1 V1 Um Stator 1 Rotor 2 Ping 62 Determine the absolute velocity at the inlet in ft/s. Choose.. Determine the blade angle at the inlet Bpt Choose...

Derive the velocities relationship between inlet and outlet.

please wright by hand and steb by steb

Question 2 A two stage, single acting, reciprocating compressor takes in air at a rate of 2 m³/s at a pressure of 1 MPa @ 16°C. The air is compressed to 0.7 MPa while running at 10 rev/s. Compression is ideal and perfect intercooling takes place. The compression process follows pV1.25 = C. Neglect clearance. Calculate: 2.1. Intermediate pressure (0.265 MPa) 2.2. Volume of LP cylinder (20 Liters) 2.3. Volume of HP cylinder (7.5 Liters) 2.4. Total cycle power (42 kW)

Pls. Answer this thank you!Steam enters a turbine stage with an enthalpy of 3628 kj/kg at 70 m/s and leaves the same stage with an enthalpy of 2846 kj/kg and a velocity of 124 m/s. Calculate the power in KW if there are 5 kg/s steam admitted at the turbine throttle.

A single stage gas turbine operates at its design condition with an axial absolute flow entry and exit from the stage. The absolute flow angle at nozzle exit is 70 degree. At stage entry the total pressure and temperature are 311 kPa and 850 oC respectively. The exhaust static pressure is 100 kPa, the total to static efficiency is 0.87 and the mean blade speed is 500 m/s. Assuming the constant axial velocity through the stage, determine the specific work done; the Mach number leaving the nozzle; the axial velocity; the total to total efficiency; the stage reaction. Take Cp = 1.148 k]/(kg°C) and y = 1.33 for the gas.

Required The developed power from the turbine The flow velocity at inlet The blade sped at inlet The blade sped at outlet The tangential component of the absolute velocity at inlet The guide vane angle The blade angle at inlet

Q2 It is proposed to design a crburettor for Maruti Car. The four strok petrol engine has a displacement (swept) of 796 cm³ and develops maximum Power at 5500 rev/min. The volumetric efficiency at this speed is assumed to be 70% and the air-fuel ratio is 13.5:1.It is expected that at peak power the theoretical air speed at the choke will be 105 m/s. the coefficient of discharge for the venturi is assumed to be 0.85 and that of the main petrol iet is 0.66. An allowance should be made for the emulsion tube, the diameter of which can be taken as 1/2.5) of the choke diameter. The petrol surface is 6mm below the choke at this engine condition. Calculate the sizes of a suitable choke and main jet. The specific gravity of petrol is 0.74. Atmospheric pressure and temperature are 1 bar and 27°C respectively. [Answers 21.3 mm, 1.183 mm ] .

A centrifugal pump running at 750r.p.m. discharges water at 0. Im3/s against a head of 10 m at its best efficiency. A second pump of the same homologous series, when working at 500r.p.m., is to deliver water at 0.05m3/s at its best efficiency. What will be the design head of the second pump and what is the scale ratio between the first and the second?

A rection turbine has guide vane angle 30° the runner blades make an angle of 80° relative to the tanget at inlet .the blades width at inlet is 1/4 of the outer diameter .the water does not have any tanget velocity at outlet.the head is 25 m and the rotational speed of the runner is 16.67 rotation per second (rps) the turbine efficiency is 88% determine the runner diameter at the inlet and the power developed by this turbine