Thrust Performance Evaluation of a Turbofan Engine Based on Exergetic Approach and Thrust Management in Aircraft
-
Enver Yalcin
Abstract
The environmental parameters such as temperature and air pressure which are changing depending on altitudes are effective on thrust and fuel consumption of aircraft engines. In flights with long routes, thrust management function in airplane information system has a structure that ensures altitude and performance management. This study focused on thrust changes throughout all flight were examined by taking into consideration their energy and exergy performances for fuel consumption of an aircraft engine used in flight with long route were taken as reference. The energetic and exergetic performance evaluations were made under the various altitude conditions. The thrust changes for different altitude conditions were obtained to be at 86.53 % in descending direction and at 142.58 % in ascending direction while the energy and exergy efficiency changes for the referenced engine were found to be at 80.77 % and 84.45 %, respectively. The results revealed here can be helpful to manage thrust and reduce fuel consumption, but engine performance will be in accordance with operation requirements.
Nomenclature
- AIMS
The Airplane Information Management System
- CC
combustion chamber
- cp
specific heat, kJ/(kg K)
energy rate, kW
exergy rate, kW
- F
fan
- h
specific enthalpy, kJ/kg
- HGT
high pressure gas turbine
- HPC
high pressure compressor
- ICAO
International Civil Aviation Organization
improvement potential, %
- K
Kelvin
- LGT
low pressure gas turbine
- LPC
low pressure compressor
mass flow rate, kg/s
- P
pressure, kPa
- s
specific entropy, kJ/(kgK)
entropy rate, kW
- T
temperature, K
work rate, kW
- Greek Letters
- ψ
specific exergy, kJ/kg
- η
efficiency
- Subscripts
- 0
reference conditions
- ch
chemical
- dest
destruction
- Ex
exergy
- f
fuel
- gen
generated
- heat
thermal
- in
inlet section
- k
kinetic
- mass
mass flow
- out
outlet section
- p
potential
- ph
physical
- work
work
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© 2017 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Study of Decay Characteristics of Hexagonal and Square Supersonic Jet
- Investigation on the Film Cooling Performance of Diffuser Shaped Holes with Different Inclination Angles
- Model-based Acceleration Control of Turbofan Engines with a Hammerstein-Wiener Representation
- Fatigue Life Prediction of Low Pressure Turbine Shaft of Turbojet Engine
- Influence of Geometry on Rotordynamic Coefficients of Brush Seal
- Numerical Investigation of Transient Flow in a Prototype Centrifugal Pump during Startup Period
- Thrust Performance Evaluation of a Turbofan Engine Based on Exergetic Approach and Thrust Management in Aircraft
- Real-time Simulation of Turboprop Engine Control System
- Ignition Study on a Rotary-valved Air-breathing Pulse Detonation Engine
Articles in the same Issue
- Frontmatter
- Study of Decay Characteristics of Hexagonal and Square Supersonic Jet
- Investigation on the Film Cooling Performance of Diffuser Shaped Holes with Different Inclination Angles
- Model-based Acceleration Control of Turbofan Engines with a Hammerstein-Wiener Representation
- Fatigue Life Prediction of Low Pressure Turbine Shaft of Turbojet Engine
- Influence of Geometry on Rotordynamic Coefficients of Brush Seal
- Numerical Investigation of Transient Flow in a Prototype Centrifugal Pump during Startup Period
- Thrust Performance Evaluation of a Turbofan Engine Based on Exergetic Approach and Thrust Management in Aircraft
- Real-time Simulation of Turboprop Engine Control System
- Ignition Study on a Rotary-valved Air-breathing Pulse Detonation Engine
