Question
In: Mechanical Engineering
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.
Solutions
samet mamat answered 1 year agoRelated Solutions
b) A 15 MW gas turbine plant operates with a two-stage compression and a two-stage expansion....
b) A 15 MW gas turbine plant operates with a two-stage
compression and a two-stage
expansion. The high-pressure turbine (HPT) drives both
low-pressure compressor
(LPC) and high-pressure compressor (HPC). A low-pressure turbine
(LPT) is connected
to a generator for electricity generation The overall pressure
ratio is 16/1 and the
maximum cycle temperature, which is at the inlet of the HPT, is
900°C. The gases
leaving the HPT are reheated to 850°C before entering the LPT.
Both compressors have
equal pressure...
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
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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
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A gas turbine operates with two stages of compression with an intercooler between the stages. Air...
A
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