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Thermodynamic-based analyses and assessments of a new-generation turbojet engine used for unmanned aerial vehicles (UAVs)

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Abstract

In this paper, exergy, sustainability, unsustainability, environmental, enviroeconomic, ecological and inefficiency assessments are done for the JP-8-fueled turbojet engine which is designed for unmanned aerial vehicles (UAVs). It is found that the combustion chamber of the turbojet engine has the minimum exergetic efficiency (12.74%) among the components, so its improvement potential is higher than other components. The gas turbine is the most sustainable component, and the combustion chamber has higher unsustainability index rate than other components. Among the components, the highest entropy generation rate is found for the combustion chamber (179.014 kW K−1) and the lowest rate is determined for the gas turbine (0.344 kW K−1). According to environmental assessment, the turbojet engine releases 22,896.38 kg carbon dioxide emission by working 10 h in a day. According to enviroeconomic assessment, the cost of the released carbon dioxide is 3319.94$ for the daily flight. According to ecological assessment, 74.5% of the fuel exergy in the combustion chamber component is not used properly.

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Abbreviations

\({c}_{\mathrm{CO}2}\) :

Carbon dioxide emission price ($ kg_CO2−1)

\({C}_{\mathrm{CO}2}\) :

Enviroeconomic index ($ day−1)

c p :

Specific heat capacity (kJ kg−1 K−1)

ex:

Specific exergy (kJ kg−1)

\(\dot{E}x\) :

Exergy rate (kW)

EXECOL:

Exergetic ecological index (-)

EXIN:

Exergetic inefficiency index (-)

\(F\) :

Thrust of the engine (kN)

IP:

Improvement potential rate (-)

LHV:

Lower heating value (kJ kg−1)

\(\dot{m}\) :

Mass flow rate (kg s−1)

P :

Pressure (kPa)

R :

Universal gas constant (kJ kg−1 K−1)

\({\dot{S}}_{\mathrm{gen}}\) :

Entropy generation rate (kW K−1)

SI :

Sustainability index (-)

t :

Working time (h day−1)

T :

Temperature (°C or K)

USI:

Unsustainability index (-)

V :

Speed (m s−1)

\(\dot{W}\) :

Work rate (kW)

\({x}_{\mathrm{CO}2}\) :

Environmental index (kg_CO2 day−1)

\({y}_{\mathrm{CO}2}\) :

Carbon dioxide emission value for thrust basis (kg_CO2 kN−1 s−1)

\(\zeta \) :

Grade function of the liquid fuel (-)

ε :

Exergy efficiency (%, -)

χ :

Relative irreversibility rate (-)

\(\delta \) :

Fuel depletion rate (-)

\(\xi \) :

Productivity lack rate (-)

0:

Dead-state (reference) condition

AC:

Air compressor

CC:

Combustion chamber

ch:

Chemical

CO2 :

Carbon dioxide

D :

Destruction

ex:

Exergy

f :

Fuel

F :

Fuel

GT :

Gas turbine

kn:

Kinetic

L :

Loss

P :

Product

ph:

Physical

pt:

Potential

thrust:

Thrust

time:

Time

AC:

Air compressor

CC:

Combustion chamber

EXECOL:

Exergetic ecological

EXIN:

Exergetic inefficiency

GT:

Gas turbine

LHV:

Lower heating value

TAI:

Turkish aerospace industries

TJE:

Turbojet engine

UAS:

Unmanned aircraft system

UAV:

Unmanned aerial vehicle

USD:

United States dollar

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Authors and Affiliations

  1. Department of Airframe and Powerplant Maintenance, School of Civil Aviation, Suleyman Demirel University, 32700, Isparta, Turkey

    Yasin Sohret

  2. Department of Mechanical Engineering, Faculty of Engineering, Usak University, 64200, Usak, Turkey

    Hakan Caliskan

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  1. Yasin Sohret
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Sohret, Y., Caliskan, H. Thermodynamic-based analyses and assessments of a new-generation turbojet engine used for unmanned aerial vehicles (UAVs). J Therm Anal Calorim 147, 11273–11288 (2022). https://doi.org/10.1007/s10973-022-11330-7

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