Entropy, Energy and Exergy for Measuring PW4000 Turbofan Sustainability
-
Hakan Aygun
Abstract
This study focuses on for a PW4000 high-bypass turbofan engine using energy, exergo-sustainable and performance viewpoint. For this aim, irreversibility and performance analyses are firstly performed for five main engine components at ≈260 kN maximum take-off thrust force. Besides, overall efficiency of the turbofan is determined to be 33 %, while propulsive and thermal efficiency of the turbofan are 72 % and 46 % respectively at 0.8 M and 288.15 K flight conditions. Secondly, calculation component-based exergetic assessment is carried out using exergetic indicators. According to the calculation, the exergetic efficiency of the engine is 32 %, while its waste exergy ratio is 0.678. Furthermore, exergetic sustainability measure is obtained as 0.473, while enviromental effect factor is 2.112. These indicators are also anticipated to help comprehend the connection between engine performance parameters and worldwide dimensions such as environmental effect and sustainable growth.
Nomenclature
- CP
-
Specific heat (kJ kg−1 K−1)
- V
-
Velocity (m.s−1)
-
-
fuel-air ratio
-
-
Mass flow rate (kg sn−1)
- h
-
Specific enthalpy (kJ kg−1)
-
-
Fuel exergy (MW)
-
-
Product exergy (MW)
- P
-
Pressure (kPa)
-
-
Rate of total anergy generation (J·s−1 )
-
-
Rate of anergy generation by shock waves (J·s−1 )
-
-
Rate of anergy generation by thermal mixing (J·s−1 )
-
-
Rate of anergy generation by viscous dissipation (J·s−1 )
-
-
Rate of exergy supplied by the engine system (J·s−1 )
-
-
Rate of mechanical exergy outflow (J·s−1 )
- Φ
-
Dissipation rate per unit volume (J s−1m−3)
- Γ
-
Weight specific aircraft energy height (m)
-
-
Viscous stress tensor (N)
- R
-
Specific gas constant (kJ kg−1 K−1)
- E
-
Energy rate, MW
- Ex
-
Exergy rate, MW
- hpr
-
Fuel heating value (kJ.kg−1)
-
-
Heat flux by conduction (J s−1)
- s
-
Specific entropy (kJ kg−1 K−1)
-
-
Relatively irreversibility
-
-
Mole fraction of component i in the exhaust gas
-
-
Flow exergy (kj/kg)
- g
-
Gibb’s free energy (kj/kmol)
- T
-
Temperature (K);Thrust(kN)
- v
-
Specific volume (m3kg−1)
- x
-
Molar fraction
- n
-
Number of moles
- ke
-
Kinetic energy
- pe
-
Potential energy
- u
-
Velocity of stream (m.s−1)
-
-
Work rate (MW)
-
-
Thrust (kN)
- MTOP
-
Maximum Take-off Operation
- TORP
-
Take-off Running Power
- BPR
-
Bypass ratio
- LPT
-
Low pressure turbine
- LPC
-
Low pressure compressor
- HPT
-
High pressure turbine
- HPC
-
High pressure compressor
- M
-
Mach number
- Greek Letters
-
-
Efficiency
- Δ
-
Difference
- π
-
Total pressure ratio
Subscripts and superscripts
- a
-
Air
- A
-
Aircraft surface area
- actl
-
Actual
- B
-
Aircraft body surface
- O
-
Outer boundary; overall
- m
-
Mechanical
- e
-
Exhaust or exit
- en
-
Exhaust nozzle
- ec
-
Exit cold
- eh
-
Exit hot
- eng
-
Engine
- tot
-
Total
- 0
-
Environment
- p
-
Propulsive
- 0,1,2 …
-
Station numbering of the engine component
- th
-
Thermal
- o
-
Overall
- c
-
Core; compressor; cold
- t
-
Turbine
- n
-
Nozzle
- LHV
-
Lower heating value
- cv
-
Control volume
- ref
-
Reference
- ch
-
Chemical
- k
-
Any k component
- dest
-
Destroyed, destruction
- ex
-
Exergy
- eef
-
Environmental effect factor
- exd
-
Exergy destruction
-
-
Waste exergy
-
-
Exergetic sustainability index
- ph
-
Physical
- re
-
Recoverable exergy
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Review
- Assessment of Exit Temperature Pattern Factors in an Annular Gas Turbine Combustor: An Overview
- Original Research Articles
- Optimization of Trenched Film Cooling Using RSM Coupled CFD
- Modeling of Relative Exergy Destruction for Turboprop Engine Components Using Deep Learning Artificial Neural Networks
- Direct Thrust Inverse Control of Aero-Engine Based on Deep Neural Network
- Entropy, Energy and Exergy for Measuring PW4000 Turbofan Sustainability
- A Centrifugal Compressor Performance Map Empirical Prediction Method for Automotive Turbochargers
- Unsteady Numerical Simulation in a Supersonic Compressor Cascade with a Strong Shock Wave
- CFD Study of Combined Impingement and Film Cooling Flow on the Internal Surface Temperature Distribution of a Vane
- CFD Analysis of Flow and Performance Characteristics of a 90°curved Rectangular Diffuser: Effects of Aspect Ratio and Reynolds Number
- Effects of the Recess Length of the Pilot Stage on the Lean Blowout Limits for the Multipoint Lean Direct Injection Combustors
- Stress and Vibration Analysis of a PDC (Pulse Detonation Chamber)
- Transverse Injection Experiments within an Axisymmetric Scramjet Combustor
Artikel in diesem Heft
- Frontmatter
- Review
- Assessment of Exit Temperature Pattern Factors in an Annular Gas Turbine Combustor: An Overview
- Original Research Articles
- Optimization of Trenched Film Cooling Using RSM Coupled CFD
- Modeling of Relative Exergy Destruction for Turboprop Engine Components Using Deep Learning Artificial Neural Networks
- Direct Thrust Inverse Control of Aero-Engine Based on Deep Neural Network
- Entropy, Energy and Exergy for Measuring PW4000 Turbofan Sustainability
- A Centrifugal Compressor Performance Map Empirical Prediction Method for Automotive Turbochargers
- Unsteady Numerical Simulation in a Supersonic Compressor Cascade with a Strong Shock Wave
- CFD Study of Combined Impingement and Film Cooling Flow on the Internal Surface Temperature Distribution of a Vane
- CFD Analysis of Flow and Performance Characteristics of a 90°curved Rectangular Diffuser: Effects of Aspect Ratio and Reynolds Number
- Effects of the Recess Length of the Pilot Stage on the Lean Blowout Limits for the Multipoint Lean Direct Injection Combustors
- Stress and Vibration Analysis of a PDC (Pulse Detonation Chamber)
- Transverse Injection Experiments within an Axisymmetric Scramjet Combustor
