Aerospace Engineering > GATE 2016 > Gas Turbine Cycles
Combustion in gas turbine engines is ideally represented as the following process:
A
Adiabatic
B
Isentropic
C
Isobaric
D
Isochoric

Correct : c

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Combustion gas turbine engines Ideal combustion process Isobaric process Aerospace Engineering GATE 2016 GATE AE 2016 Q19 Gas turbine thermodynamics Combustion process representation Aerospace engineering combustion principles

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