Question

In the compressor side of a turbocharger, the radial component of the velocity at the exit...

In the compressor side of a turbocharger, the radial component of the velocity at the exit of a radial vaned impeller is 28 m/s and the slip factor is 0.9. The impeller tip speed is 350 m/s. The impeller area is 0.08 m2 and the total-to-total efficiency is 90%. Stagnation pressure and temperature at the inlet of the compressor are 1 bar and 288 K. In the turbine side, the gases (with stagnation conditions of 390 kPa and 1150 K) enter blades of the turbine radially and leave without exit swirl. Blades of the turbine at the inlet are radial. Inlet diameter of the turbine is 12.6 cm. The ratio of specific heats is 1.35 and outlet static pressure is 150 kPa and the mass flow rate is 0.28 kg/s. Determine: (a) exit Mach number of the compressor, (b) mass flow rate through the compressor, (c) isentropic work of the turbine, (d) power delivered by the turbine, (e) blade speed at the inlet of the turbine.
Engineering   Mechanical-Engineering   
0 0
Add a commentTranscribed image text
Next >

Homework Answers

Answer #1

0 0
Know the answer?
Your Answer:

Post as a guest

Your Name:

What's your source?

Earn Coins

Coins can be redeemed for fabulous gifts.

Log In

Sign Up

Not the answer you're looking for?
Ask your own homework help question
Similar Questions
A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a...
A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as the compressor. Air enters the diffuser with a volumetric flow rate of 63.7 m3/s at 40 kPa, 240 K, and a velocity of 180 m/s, and decelerates essentially to zero velocity. The compressor pressure ratio is 10 and the compressor has an isentropic efficiency of 85%. The turbine inlet temperature is 1240 K, and its isentropic efficiency is 85%. The...
Q1. An ideal jet engine with a compressor, combustion chamber, turbine and converging nozzle was held...
Q1. An ideal jet engine with a compressor, combustion chamber, turbine and converging nozzle was held stationary during an experiment to measure thrust in a laboratory. The turbine is used to drive the compressor. The atmospheric pressure and room temperature in the laboratory is measured as 102 kPa and 283 K. The gauge pressure at compressor exit is measured as 0.0781 bar and the inlet air flow is 10.4414 l/s. The maximum temperature reached in the jet engine is measured...
An aircraft flies with a Mach number Ma1=0.921 at an altitude of 7021 m where the...
An aircraft flies with a Mach number Ma1=0.921 at an altitude of 7021 m where the pressure is 42.1 kPa and the temperature is 242.1 K. Calculate the stagnation properties (static temperature, pressure, density), cross-section areas A1 and A2=? at the inlet and outlet of the diffuser. The diffuser at the engine inlet has an exit Mach number of Ma2=0.3. For a mass flow rate of 32.1 kg/s, determine the static pressure rise across the diffuser and the exit area....
NO INTERPOLATION REQUIRED Air enters an adiabatic turbine at 1000 kPa and 1625 degrees C (state...
NO INTERPOLATION REQUIRED Air enters an adiabatic turbine at 1000 kPa and 1625 degrees C (state 1) with a mass flow rate of 5 kg/s and leaves at 100 kPa the isentropic efficiency of the turbine is 85%. Neglecting the kinetic energy change of the steam, and considering variable specific heats, determine: a. the isentropic power of the turbine Isentropic power in kW b. the temperature at the turbine exit temperature at exit in degrees C c. the actual power...
A two-part compressor operates with steady state conditions. The exit of the first part of the...
A two-part compressor operates with steady state conditions. The exit of the first part of the compressor is also the inlet of the second part of the compressor. In the first part of the compressor, air is compressed from 1.5 bar, 350 K to 5.5 bar with a mass flow rate of 7.2 kg/sec. In the second part of the compressor, air is compressed from 5.5 bar to 9.5 bar with a mass flow rate of 5.8 kg/sec. Each unit...
An air turbine with inlet conditions of 500 kPa, 327 C operates in steady flow and...
An air turbine with inlet conditions of 500 kPa, 327 C operates in steady flow and has an actual power output of 70 kW. The discharge pressure is 100 kPa and the turbine has an efficiency of 0.8 at these operating conditions. Consider specific heats constant. a) Calculate the actual mass flow rate at the turbine exit. b) Calculate the actual turbine exit temperature. c) Show the actual and ideal processes on a T-s and P-v diagram.
An axial-flow compressor rotor at the pitchline has a radius of rm = 0.3 m. The...
An axial-flow compressor rotor at the pitchline has a radius of rm = 0.3 m. The shaft rotational speed is ? =4500 rpm. The inlet flow to the rotor has zero preswirl and the axial velocity is Cz1 = Cz2 = Cz3 = 180 m∕s. The rotor has a 50% degree of reaction at the pitchline. The stage adiabatic efficiency is nearly equal to the polytropic efficiency ?s ≅ ec = 0.90. Assuming the inlet total temperature is Tt1 =...
Air is expanded isentropically in an adiabatic turbine, to produce 115 kW of power. If the...
Air is expanded isentropically in an adiabatic turbine, to produce 115 kW of power. If the mass flow rate is 0.75 kg/s, and the air at the exit is 500 K and 155 kPa, then what is the temperature and pressure at the inlet of the turbine? (a) The temperature is? K (b) The pressure is? kPa NOTE: Do NOT approximate the air as having a constant specific heat.
A turbojet aircraft is flying with a velocity of 320 m/s at a certain altitude, where...
A turbojet aircraft is flying with a velocity of 320 m/s at a certain altitude, where the ambient conditions are 32 kPa and -32°C. The pressure ratio across the compressor is 12, and the temperature at the turbine inlet is 1400K. Air enters the compressor at a rate of 40 kg/s, and the and the jet fuel has a heating value of 42700 kJ/kg. Assuming ideal operations for all components and constant specific heats for air at room temperature, (Cp=1.005...
A steam turbine has inlet steam pressure p1 = 1.4 MPa absolute. Inlet steam temperature is...
A steam turbine has inlet steam pressure p1 = 1.4 MPa absolute. Inlet steam temperature is T1 = 400 oC. This corresponds to inlet enthalpy per unit mass of h1 = 3121 kJ/kg. Exit pressure of the steam is p2 = 101 kPa absolute. Exit steam temperature is T2 = 100 oC. This corresponds to exit enthalpy per unit mass of h2 = 2676 kJ/kg. Inlet speed of the steam is V1 = 15 m/s and exit speed is V2...
ADVERTISEMENT
Need Online Homework Help?

Get Answers For Free
Most questions answered within 1 hours.

Ask a Question
ADVERTISEMENT