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, Np = 0.99 Ambient conditions, pa, Ta, 1.013 bar, 288 K Ignore inlet and exhaust losses, draw cycle on T- s diagram and calculate: а) Turbine pressure ratio. b) The net specific output work. c) The gas turbine 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, Np = 0.99 Ambient conditions, pa, Ta, 1.013 bar, 288 K Ignore inlet and exhaust losses, draw cycle on T- s diagram and calculate: а) Turbine pressure ratio. b) The net specific output work. c) The gas turbine thermal efficiency.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

2.7). A simple gas turbine, has the following data:
Compressor pressure ratio,
Tp = 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,
Np = 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:
a)
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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