Question
In: Mechanical Engineering
An industrial gas turbine operates at an 8.8:1 pressure ratio and a mass flow of 77...
An industrial gas turbine operates at an 8.8:1 pressure ratio
and a mass flow of 77 kg/s. The
exhaust temperature is at 437?C and the inlet temperature to the
machine is around 1000?C.
The machine is to be designed for a constant axial velocity of 200
m/s. (This data is based on
the Rolls-Royce Avon, an engine that dates from the 1950s but is
still used as low efficiency
high reliability engine for stationary power such as pipeline
pumping.)
For this gas turbine, draw to scale the meridional view with:
(a) a constant mean radius of 0.4 m.
(b) a constant outer diameter (to minimise cross sectional area) of
1.05 m.
Solutions
samet mamat answered 2 years agoRelated Solutions
An industrial gas turbine operates at an 8.8:1 pressure ratio and a mass flow of 77...
An industrial gas turbine operates at an 8.8:1 pressure ratio
and a mass flow of 77 kg/s. The
exhaust temperature is at 437?C and the inlet temperature to the
machine is around 1000?C.
The machine is to be designed for a constant axial velocity of 200
m/s. (This data is based on
the Rolls-Royce Avon, an engine that dates from the 1950s but is
still used as low efficiency
high reliability engine for stationary power such as pipeline
pumping.)
For...
A gas turbine power plant operates on a Brayton cycles has a pressure ratio of 7....
A gas turbine power plant operates on a Brayton cycles
has a pressure ratio of 7. Air enters the
compressor at 300 K. The energy in the form of heat is transferred
to the air in the amount of 950
kJ/kg. Using a variable specific heat for air and assuming the
compressor isentropic efficiency is
83 percent and turbine isentropic efficiency is 85 percent.
Determine the followings:
(i) The highest temperature in the cycle [5 marks]
(ii) The net work...
A gas turbine unit has a pressure ratio of 5/1 and a maximum cycle temperature of...
A gas turbine unit has a pressure ratio of 5/1 and a maximum
cycle temperature of 550⁰C. The turbine drives the compressor and
an electric generator., the mechanical efficiency of the drive
being 97%. The ambient temperature is 20⁰C and the isentropic
efficiencies of the compressor and turbine are 0.8 and 0.83
respectively.
Calculate the power output in kilowatts for an airflow of
15kg/s. Calculate also the thermal efficiency and the work ratio.
Neglect changes in kinetic energy, and the...
A gas turbine plant consists of a compressor with a pressure ratio of 10, a combustion...
A gas turbine plant consists of a compressor with a pressure
ratio of 10, a combustion chamber, and a turbine mounted on the
same shaft as the compressor; the net electrical power of the unit
is 20 MW. The inlet air conditions are 1.013 bar and 15 ?C and the
maximum cycle temperature is 1100 K. The exhaust gases from the
turbine are passed through a heat exchanger to heat water for space
heating before passing to the chimney; by...
A gas turbine air- standard cycle operates between a low pressure of 14.7 Psia and a...
A gas turbine air- standard cycle operates between a low
pressure of 14.7 Psia and a high pressure of 60 Psia. The
temperature of the gas at the inlet to the compressor and turbine
are 60 and 1000 respectively. If 40,000 ft3 /min. of air enter the
compressor and assuming k=1.41, compute:
a) The theoretical net power output, and
b) The air – standard thermal efficiency
In a marine gas turbine unit a high-pressure turbine drives the compressor, and a low-pressure turbine...
In a marine gas turbine unit a high-pressure turbine drives the
compressor, and a low-pressure turbine drives the propeller through
suitable gearing. The overall pressure ratio is 4/1, and the
maximum temperature is 650⁰C. The isentropic efficiencies of the
compressor, High Pressure turbine, and Low Pressure turbine are
0.8, 0.83 and 0.85 respectively, and the mechanical efficiency of
both shafts is 98%.
Calculate the pressure entering the Low Pressure turbine when
the air intake conditions are 1.01 bar and 25⁰C....
In a gas turbine plant, air is compressed through a pressure ratio of 6 from 15...
In a gas turbine plant, air is compressed through a pressure
ratio of 6 from 15 ?C. It is then heated to the maximum permissible
temperature of 750 ?C and expanded in two stages each of expansion
ratio ?6, the air being reheated between the stages to 750 ?C. A
heat exchanger allows the heating of the compressed air through 75
percent of the maximum range possible. Calculate the cycle
efficiency, the work ratio and the net work output per...
In a gas turbine with two-stage compression and expansion, the total pressure ratio is 12. Air...
In a gas turbine with two-stage compression and expansion, the
total pressure ratio is 12. Air enters the compressor at a
temperature of 320 K and the turbine at a temperature of 1320 K.
The isanthropic efficiency of the compressors is 75%, the
efficiency of the turbines is 87% and the regenerator is 78%.
Considering the change of specific temperatures with
temperature;
a) back work rate,
b) calculate the thermal efficiency of the cycle.
An ideal Rankine cycle operates with a turbine inlet pressure of 600 psia and a turbine...
An ideal Rankine cycle operates with a turbine inlet pressure of
600 psia and a turbine inlet temperature of 526 oF. The steam is
isentropically expanded through the turbine to 15 psia as
illustrated on the T-s diagram shown below. Using the Mollier
diagram, determine the enthalpy at the turbine inlet, in BTU/lbm,
under these operating conditions. State your answer in whole
numbers.
An ideal Rankine cycle operates with a turbine inlet pressure of 900 psia and a turbine...
An ideal Rankine cycle operates with a turbine inlet pressure of
900 psia and a turbine inlet temperature of 572 oF. The steam is
isentropically expanded through the turbine to 5 psia as
illustrated on the T-s diagram shown below. Using the Mollier
diagram, determine the percent moisture at the turbine outlet under
these operating conditions. State your answer in whole numbers.
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