Simple thermodynamics of jet engines | Zendy

P. Patrı́cio | Zendy; J. M. Tavares | Zendy

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Simple thermodynamics of jet engines

Author(s) -

P. Patrı́cio,

J. M. Tavares

Publication year - 2010

Publication title -

american journal of physics

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.541

H-Index - 99

eISSN - 1943-2909

pISSN - 0002-9505

DOI - 10.1119/1.3373924

Subject(s) - thermal efficiency , thrust , physics , jet engine , heat engine , thermodynamics , turbine , gas compressor , jet (fluid) , compression ratio , thermal , mechanics , simple (philosophy) , chemistry , internal combustion engine , combustion , philosophy , organic chemistry , epistemology

We use the first and second laws of thermodynamics to analyze the behavior of an ideal jet engine. Simple analytical expressions for the thermal efficiency, the overall efficiency, and the reduced thrust are derived. We show that the thermal efficiency depends only on the compression ratio r and on the velocity of the aircraft. The other two performance measures depend also on the ratio of the temperature at the turbine to the inlet temperature in the engine, T3/Ti. An analysis of these expressions shows that it is not possible to choose an optimal set of values of r and T3/Ti that maximize both the overall efficiency and thrust. We study how irreversibilities in the compressor and the turbine decrease the overall efficiency of jet engines and show that this effect is more pronounced for smaller T3/Ti.

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