2.6).A gas-turbine plant operates on the regenerative Brayton cycle with two stages of reheatingand two stages of intercooling between the pressure limits of 100 and 1200 kPa. The workingfluid is air. The air enters the first and theRegeneratorsecond stages of the compressor at 300 Kand 350 K, respectively, and the first andReheaterthe second stages of the turbine atComb.cham.1400 Kand1300 K, respectively.6WnetAssuming both the compressor and theComp. IComp. IITurb. ITurb. IIturbine have an isentropic efficiency of80% andthe regenerator hasaneffectiveness of 75%, determine (a) theFig. p2.6.Intercoolerback-work ratio and the network output,For two-stage compression and expansion, thework input is minimized and the work output ismaximized when both stages of the compressorand the turbine have the same pressure ratio.and (b) the thermal efficiency.2.7).A simple gas turbine, has the following data:Compressor pressure ratio,p = 20Turbine inlet temperature,T3= 1400 KCompressor isentropic efficiency,Nc = 0.87Turbine isentropic efficiency,Ne = 0.9Combustor pressure loss,AP = 5%Combustion efficiency,Пь 3 0.99Ambient conditions, Pa, Ta,1.013 bar, 288 KIgnore inlet and exhaust losses, draw cycle on T - s diagram and calculate:a)Turbine pressure ratio.b)The net specific output work.c)The gas turbine thermal efficiency.2.8).For the simple gas turbine, in problem (2.7), which produces 100 MW, calculate:а)Air mass flow rate.b)Fuel mass flow rate if the calorific value of kerosene fuel burned is 43.2 MJ/kg.c)Theoretical air to fuel ratio.

Isentropic efficiency of turbine and compressor is 80% Effectiveness of regenerator is 75% find a)…

2.6). A gas-turbine plant operates on the regenerative Brayton cycle with two stages of reheating and two stages of intercooling between the pressure limits of 100 and 1200 kPa. The working fluid is air. The air enters the first and the Regenerator second stages of the compressor at 300 K and 350 K, respectively, and the first and Reheater the second stages of the turbine at Comb. cham. 1400 K and 1300 K, respectively. 6 Wnet Assuming both the compressor and the Comp. I Comp. II Turb. I Turb. II turbine have an isentropic efficiency of 3 80% and the regenerator has an effectiveness of 75%, determine (a) the Fig. p2.6. Intercooler back-work ratio and the network output, For two-stage compression and expansion, the work input is minimized and the work output is and (b) the thermal efficiency. maximized when both stages of the compressor

2.6). A gas-turbine plant operates on the regenerative Brayton cycle with two stages of reheating and two stages of intercooling between the pressure limits of 100 and 1200 kPa. The working fluid is air. The air enters the first and the Regenerator second stages of the compressor at 300 K and 350 K, respectively, and the first and Reheater the second stages of the turbine at Comb. cham. 1400 K and 1300 K, respectively. 6 Wnet Assuming both the compressor and the Comp. I Comp. II Turb. I Turb. II turbine have an isentropic efficiency of 3 80% and the regenerator has an effectiveness of 75%, determine (a) the Fig. p2.6. Intercooler back-work ratio and the network output, For two-stage compression and expansion, the work input is minimized and the work output is and (b) the thermal efficiency. maximized when both stages of the compressor

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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Problem 1.1MA

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Question

2.6).
A gas-turbine plant operates on the regenerative Brayton cycle with two stages of reheating
and two stages of intercooling between the pressure limits of 100 and 1200 kPa. The working
fluid is air. The air enters the first and the
Regenerator
second stages of the compressor at 300 K
and 350 K, respectively, and the first and
Reheater
the second stages of the turbine at
Comb.
cham.
1400 K
and
1300 K, respectively.
6
Wnet
Assuming both the compressor and the
Comp. I
Comp. II
Turb. I
Turb. II
turbine have an isentropic efficiency of
80% and
the regenerator has
an
effectiveness of 75%, determine (a) the
Fig. p2.6.
Intercooler
back-work ratio and the network output,
For two-stage compression and expansion, the
work input is minimized and the work output is
maximized when both stages of the compressor
and the turbine have the same pressure ratio.
and (b) the thermal efficiency.
2.7).
A simple gas turbine, has the following data:
Compressor pressure ratio,
p = 20
Turbine inlet temperature,
T3
= 1400 K
Compressor isentropic efficiency,
Nc = 0.87
Turbine isentropic efficiency,
Ne = 0.9
Combustor pressure loss,
AP = 5%
Combustion efficiency,
Пь 3 0.99
Ambient conditions, Pa, Ta,
1.013 bar, 288 K
Ignore inlet and exhaust losses, draw cycle on T - s diagram and calculate:
a)
Turbine pressure ratio.
b)
The net specific output work.
c)
The gas turbine thermal efficiency.
2.8).
For the simple gas turbine, in problem (2.7), which produces 100 MW, calculate:
а)
Air mass flow rate.
b)
Fuel mass flow rate if the calorific value of kerosene fuel burned is 43.2 MJ/kg.
c)
Theoretical air to fuel ratio.

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REFERENCE: FROM BOOK - ENGINEERING THERMOFLUIDS, M. MASSOUD
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