Question
In: Mechanical Engineering
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. Calculate also the thermal efficiency and the shaft power when the mass air flow is 60 kg/s. Neglect kinetic energy changes, and the pressure loss in combustion.
For all compression processes take cp = 1.005 kJ/kg K and ɣ=1.4; for the combustion and expansion processes take cp = 1.15 kJ/kg K and ɣ=1.333. Neglect the mass of fuel.
Solutions
samet mamat answered 1 year agoRelated Solutions
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
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 study was conducted on a high-pressure inlet fogging method for a gas turbine engine. Researchers...
A study was conducted on a high-pressure inlet fogging method
for a gas turbine engine. Researchers considered two models.
Partial output is provided below.
Source
Df
SS
MS
F
Regression
5
148526859
29705372
94
Error
61
19370350
317547
Total
???
167897208
Source
Df
SS
MS
F
Regression
???
142586570
47528857
???
Error
63
25310639
401756
Total
???
167897208
Answer the following questions rounding off at the nearest
integer.
The number of observations collected for the study is equal
to
The...
A study was conducted on a high-pressure inlet fogging method for a gas turbine engine. Researchers...
A study was conducted on a high-pressure inlet fogging method
for a gas turbine engine. Researchers considered two models.
Partial output is provided below.
Source
Df
SS
MS
F
Regression
5
148526859
29705372
94
Error
61
19370350
317547
Total
???
167897208
Source
Df
SS
MS
F
Regression
???
142586570
47528857
???
Error
63
25310639
401756
Total
???
167897208
Answer the following questions rounding off at the nearest
integer.
1. The number of observations collected for the study is equal
to...
a) An open cycle gas turbine engine consists of a compressor, a combustion chamber and a...
a) An open cycle gas turbine engine consists of a compressor, a
combustion chamber and a two-stage turbine with a re-heater. The
gas enters the compressor at a temperature of 15 C. The pressure
ratio of the compressor, which is 90% efficient, is 12. The
combustion gas enters the first stage turbine at 1100 C. Both
stages of the turbine are 95% efficient. The first stage has a
pressure ratio of 4, whereas that of the second stage is 3....
The temperature and pressure of the steam at the inlet of a high pressure turbine is...
The temperature and pressure of the steam at the inlet of a high pressure turbine is 500 ° C, respectively. It is 12 MPa and 300 ° C and 3MPa at its outlet. If the mass flow of steam is 400 kg / h, how much is the isentropic efficiency of the turbine?
. In a gas turbine plant, air enters a compressor at atmospheric conditions of 15 ?C,...
. In a gas turbine plant, air enters a compressor at atmospheric
conditions of 15 ?C, 1.0133 bar and is compressed through a
pressure ratio of 10. The air leaving the compressor passes through
a heat exchanger before entering the combustion chamber. The hot
gases leave the combustion chamber at 800 ?C and expand through an
HP turbine which drives the compressor. On leaving the HP turbine
the gases pass through a reheat combustion chamber which raises the
temperature of...
. Air enters the compressor of a gas turbine power plant operating on Brayton cycle at...
. Air enters the compressor of a gas turbine power plant
operating on Brayton cycle at 14.5 psia and 540° R. The pressure
ratio across the turbine and compressor is same, which is equal to
6. Assume that the compressor work as 0.4 times the turbine work.
Take K=1.4 a) Draw the T-S diagram of the cycle. [2] b) Calculate
the maximum temperature in the cycle. [3] c) Calculate the cycle
efficiency
Air enters the compressor of a simple gas turbine at p1 = 14 lbf/in2, T1 =...
Air enters the compressor of a simple gas turbine at
p1 = 14 lbf/in2, T1 = 520°R. The
isentropic efficiencies of the compressor and turbine are 83 and
87%, respectively. The compressor pressure ratio is 16 and the
temperature at the turbine inlet is 2500°R. The volumetric flow
rate of the air entering the compressor is 9000 ft3/min.
Use an air-standard analysis.
Determine all temperatures at each state.
A) Determine the net power developed, in Btu/h.
B) Determine the thermal...
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