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Exergetic and Environmental Analyses of Turbojet Engine

  • Burak YukselEmail author
  • Ozgur Balli
  • Huseyin Gunerhan
  • Arif Hepbasli
  • Halil Atalay
Conference paper
Part of the Green Energy and Technology book series (GREEN)

Abstract

This study deals with exergetic and environmental analyses of turbojet engine used on the military training aircrafts. In the analysis, the engine data measured in the Engine Test Cell at First Air Maintenance and Factory Directorate of Turkish Air Forces in Eskisehir, Turkey are utilized. The exergy balance equations are derived for each component of the engine along with the overall the engine. Several thermodynamic parameters (the fuel exergy depletion ratio, the productivity lack ratio, the relative exergy consumption ratio, exergetic improvement potential, exergetic improvement potential ratio, relative exergetic improvement potential, exergetic fuel-product ratio, and sustainability index) are used to evaluate the performance of the engine and its main components (the air compressor, the combustion chamber, the gas turbine, the exhaust forward duct, the aft exhaust duct, and the mechanical shaft). Exergy losses and destructions are investigated to determine thermodynamic inefficiencies. The exergetic efficiency of the engine is determined to be 18.77%. The highest exergy destruction rate of 2921.01 kW in the engine occurs within the combustion chamber. The mechanical shaft of the engine has the maximum sustainability index of 100.65. An environmental analysis of the engine is also performed.

Keywords

Turbojet engine Exergy analysis Exergy efficiency Sustainability index Environmental analysis 

Nomenclature

.

\(c_{\text{P}}\)

Specific heat capacity (kJ kg−1 K−1)

\({\dot{\text{E}}}{\text{x}}\)

Exergy rate (kW)

\({\dot{\text{E}}}{\text{xIP}}\)

Exergetic improvement potential (kW)

\({\dot{\text{E}}}{\text{xIPR}}\)

Exergetic improvement potential rate ratio (%)

\({\text{LHV}}\)

Lower heating value of fuel (kJ kg−1)

\(\dot{m}\)

Mass flow rate (kg s−1)

p

Pressure (kPa)

\({\text{R}}{\dot{\text{E}}}{\text{xIP}}\)

Relative improvement potential rate (%)

SI

Sustainability index (–)

T

Temperature (K)

\(\dot{W}\)

Work rate or power (kW)

Greek Letters

\(\alpha\)

Fuel exergy depletion ratio (%)

\(\beta\)

Productivity lack ratio in exergetic term (%)

\(\chi\)

Relative exergy consumption ratio (%)

\(\gamma\)

Fuel exergy grade function

\(\psi\)

Exergy (second law) efficiency (%)

Subscripts

a

Air

AC

Air compressor

C

Consumption

CC

Combustion chamber

cg

Combustion gases

D

Destroyed, destruction

EAD

Exhaust aft duct

EFD

Exhaust forward duct

GT

Gas turbine

GTMS

Gas turbine mechanical shaft

in

Input

out

Output

P

Pressure

Pr

Product

ref

Reference

T

Temperature

TJE

Turbojet engine

Abbreviations

AC

Air compressor

EAD

Exhaust aft duct

EFD

Exhaust forward duct

CC

Combustion chamber

GT

Gas turbine

GTMS

Gas turbine mechanical shaft

TJE

Aircraft jet engine

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Copyright information

© Springer Nature Switzerland AG 2020

Authors and Affiliations

  • Burak Yuksel
    • 1
    Email author
  • Ozgur Balli
    • 1
  • Huseyin Gunerhan
    • 1
  • Arif Hepbasli
    • 1
  • Halil Atalay
    • 1
  1. 1.Mechanical Engineering Department, Faculty of EngineeringEge UniversityAnkaraTurkey

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