Question
In: Mechanical Engineering
An ideal gas-turbine cycle with two stages of compression and two stages of expansion. The overall...
An ideal gas-turbine cycle with two stages of compression and two stages of expansion. The overall pressure ratio is 9. The air enters each stage of the compressor at 300 K and each stage of the turbine at 1200 K. assuming an efficiency of 86 percent for each compressor stage and an efficiency of 90 percent for each turbine stage. Draw the T-S diagram and determine the back work ratio and the thermal efficiency of the cycle, assuming (a) no regenerator is used and (b) a regenerator with 85 percent effectiveness is used.
Solutions
samet mamat answered 1 month agoRelated Solutions
For an ideal gas-turbine cycle with two stages of compression and two stages of expansion, the...
For an ideal gas-turbine cycle with two stages of compression
and two stages of expansion, the pressure ratio across each stage
of the compressor and turbine is 3. The air enters each stage of
the compressor at 300 K and each stage of the turbine at 1200K.
Using variable specific heats, determine the back work ratio and
the thermal efficiency of the cycle, assuming
(a)no regenerator is used,
(b)a regenerator with 75% effectiveness is used.
Consider an ideal gas-turbine cycle with two stages of compression and two stages of expansion. The...
Consider an ideal gas-turbine cycle with two stages of
compression and two stages of expansion. The pressure ratio across
each stage of the compressor and turbine is 3. The air enters each
stage of the compressor at 300 K and each stage of the turbine at
1200 K. Determine the back work ratio and the thermal efficiency of
the cycle, assuming (a) the expansion and compression processes to
be isentropic and no regenerator is used, (b) the expansion and
compression...
Consider an ideal gas turbine cycle with two stages of compression and two stages of expansion. The...
Consider an ideal gas turbine cycle with two stages of
compression and two stages of expansion. The pressure
ratio across each compressor stage and each turbine stage is 5 to
1. The pressure at the entrance to the first compresor is 100 kPa,
the temperature entering each compressor is 25°C (298 K), and the
temperature entering each turbine is 1100°C (1373 K). An ideal
regenerator is also incorporated into the cycle. For the
air involved, it may be assumed that Cp =...
Consider an ideal gas-turbine cycle with two stages of compression and two stages of expansion. The...
Consider an ideal gas-turbine cycle with two stages of
compression and two stages of expansion. The pressure ratio across
each stage of the compressor and turbine is 3. The air enters each
stage of the compressor at 300 K and each stage of the turbine at
1200 K. Use variable specific heats. Assuming an efficiency of 86
percent for each compressor stage and an efficiency of 90 percent
for each turbine stage.
(a) no regenerator is used
rbw=rbw= % (Round...
Assume you are working on an ideal gas-turbine cycle that has three stages of compression with...
Assume you are working on an ideal gas-turbine cycle that has
three stages of compression with intercooling and three stages of
expansion with reheating at 100 kPa and 290 K. This system uses a
regenerator as well. The pressure ratio across each stage of the
compressor and turbine is 3; the air temperature when entering the
turbine is 1300 K; and the regenerator operates perfectly. Draw the
T − s diagram of this system. Determine the mass flow rate of...
A regenerative gas-turbine power plant with two stages of compression and two stages of expansion operates...
A regenerative gas-turbine power plant with two stages of
compression and two stages of expansion operates on a Brayton cycle
with a pressure ratio across the two-stage compressor of 12. Air
enters the first stage of the compressor at 100 kPa and 300 K. At
the intercooler exit, the temperature is 300 K. In both turbine
stages, air enters at 1400 K. The total heat transfer rate to the
air in both combustors is 5,000 kW. The regenerator has an...
A gas turbine operates with two stages of compression with an intercooler between the stages. Air...
A
gas turbine operates with two stages of compression with an
intercooler between the stages. Air enters the first stage at 100
kPa and 300 K. The pressure ratio across each compressor stage is 5
to 1 and each stage has an isentropic efficiency of 85%. Air exits
the intercooler at 330 K. The maximum cycle temperature is 1500 K
and the cycle has a single turbine stage that works isentropically.
Calculate the mass flow rate of the air if...
A gas turbine operates with two stages of compression with an intercooler between the stages. Air...
A
gas turbine operates with two stages of compression with an
intercooler between the stages. Air enters the first stage at 100
kPa and 300 K. The pressure ratio across each compressor stage is 5
to 1 and each stage has an isentropic efficiency of 85%. Air exits
the intercooler at 330 K. The maximum cycle temperature is 1500 K
and the cycle has a single turbine stage that works isentropically.
Calculate the exit temperature of each compressor stage and...
In a gas turbine generating station the overall compression ratio is 12/1, performed in three stages...
In a gas turbine generating station the overall compression
ratio is 12/1, performed in three stages with pressure ratios of
2.5/1, 2.4/1, and 2/1 respectively. The air inlet temperature to
the plant is 25 ℃ and intercooling between the stages reduces the
temperature to 40 ℃. The HP turbine drives the HP and
intermediate-pressure compressor stages; the LP turbine drives the
LP compressor and the generator. The gases leaving the LP turbine
passed through the heat exchanger which heats the...
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.
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