Question

An adiabatic air compressor compresses 10.6 L/s of air at 120
kPa and 20°C to 1000 kPa and 300°C. The constant pressure specific
heat of air at the average temperature of 160°C = 433 K is
*c _{P}* = 1.018 kJ/kg·K. The gas constant of air is

Answer #1

air pressure of 103 kPa., entering the compressor at a
temperature of 15 degrees Celsius and a low speed. 1 mPa pressure,
336 degrees Celsius temperature and 106 m / s speed is coming out
of the compressor. The compressor is cooled by air at a temperature
of 15 degrees Celsius and 26 kW. The power input to the compressor
is 298 kW. (cp= 1.005kj/kgK , R=0.287 kj/kgK)
a) Find the mass flow of air
b) calculate the irreversibility in...

Use cold-air-standard analysis with the fluid modeled as an
ideal gas with R=0.287 kJ/kg-K and constant k=1.4. Neglect changes
in kinetic and potential energy. Consider a SSSF of air at 300 K
and 100 kPa entering the compressor of a Simple Brayton Cycle Gas
Turbine powerplant. The cycle pressure ratio is 40 and maximum
cycle temperature is 1800 K. For compressor isentropic efficiency
of 82% the compressor work input per unit mass = __ kJ/kg (enter
the nearest positive integer...

Q#1 An adiabatic compressor receives air from the
ambient at 95 kPa, 20°C, with a low velocity. At the compressor
discharge, air exits at 1.52 MPa, 430°C. The power input to the
compressor is 5000 kW. Determine the mass flow rate of air through
the compressor.

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.

In a cylinder/piston arrangement, air is compressed in a
reversible polytropic process to a final state of 800 kPa, 500 K.
Initially air is at 110 kPa and 25oC. During the
compression process heat transfer takes place with the ambient
maintained at 25oC. Assume air as an ideal gas (R =0.287
kJ/kg) and has constant specific heats of Cp = 1.004
kJ/kgK and Cv = 0.717 kJ/kgK. If the mass of air in the
cylinder is 0.1286 kg, determine
a)...

A Diesel cycle engine is analyzed using the air standard
method. Given the conditions at state 1, compression ratio
(r), and cutoff ratio (rc) determine the efficiency and other
values listed below.
Note: The gas constant for air is R=0.287 kJ/kg-K.
--Given Values--
T1 (K) = 322
P1 (kPa) = 120
r = 11.5
rc = 1.6
Specific internal energy (kJ/kg) at state 1: 229.86
Relative specific volume at state 1= 520.52
Relative specific volume at state 2= 45.26
Temperature...

A Diesel cycle engine is analyzed using the air standard
method. Given the conditions at state 1, compression ratio
(r), and cutoff ratio (rc) determine the efficiency and other
values listed below.
Note: The gas constant for air is R=0.287 kJ/kg-K.
--Given Values--
T1 (K) = 322
P1 (kPa) = 120
r = 11.5
rc = 1.6
Specific internal energy (kJ/kg) at state 1: 229.86
Relative specific volume at state 1= 520.52
Relative specific volume at state 2= 45.26
Temperature...

Consider a cold air-standard Diesel cycle. At the beginning of
compression, 102 kPa, and 300 K. The mass of air is 0.120 kg, the
compression ratio is 16, and the cut-off ratio is 2.0
For a cold air-standard analysis use the following values: cp =
1.005 kJ/kgK, cv = 0.718 kJ/kgK, k=1.40, M=28.97 kg/kmol.
Determine the following :
(a) pressure at end of compression stroke, in kPa
(b) temperature at end of compression stroke, in K
(c) maximum temperature in...

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 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...

ADVERTISEMENT

Get Answers For Free

Most questions answered within 1 hours.

ADVERTISEMENT

asked 4 minutes ago

asked 4 minutes ago

asked 5 minutes ago

asked 5 minutes ago

asked 6 minutes ago

asked 11 minutes ago

asked 12 minutes ago

asked 15 minutes ago

asked 15 minutes ago

asked 15 minutes ago

asked 15 minutes ago

asked 19 minutes ago