T. Hikmet Karakoc

Exergetic and exergo–economic analysis of a turboprop engine: a case study for CT7–9C

The turboprop engine has played an important role in short haul commuter and military transport aircraft where high speed is not critical. It may provide the aviation sector with one of the most significant means of achieving reduced operating costs through reductions in fuel consumption. This paper deals with exergo–economic analysis of a modern turboprop engine (CT7–9C) with a free power turbine used for a medium–range twin–engine transport plane that was jointly developed as a regional airliner and military transport. The investigated main components of the engine are the compressor, the combustor, the gas generator, the power turbine and the exhaust. Exergetic parameters, along with exergo–economic parameters, have been calculated for each engine component.

Component–based exergetic measures of an experimental turboprop/turboshaft engine for propeller aircrafts and helicopters

In this paper, component–based exergetic assessment is presented for an experimental turboprop/turboshaft engine, including comparisons and exergetic performance such as their efficiencies, improvement potentials, exergy destruction rates, relative exergy destructions, fuel depletion ratios, productivity lacks, and fuel and product exergy factors with different power settings and torques. The exergetic assessment of the engine components provided here should be helpful for designing shaft–power aero engines. Results from this study also evaluate effects of the operating parameters on the exergetic performance of the engine components commonly used in regional propeller aircrafts and helicopters.

Exergy analysis of a turbofan aircraft engine

An exergy analysis is reported for a General Electric turbofan engine (the CF6-80) using sea-level data. The effects on exergy efficiencies and exergy destructions are investigated of modifying the isentropic efficiencies of turbomachinery components. The most irreversible units in the system are found to be the fan and the core engine exhaust, with exergy loss rates of 47.3 MW and 35.9 MW, respectively, and the combustion chamber, with an exergy destruction rate of 31.5 MW. The exergy efficiencies of the fan and the core engine exhausts are found to be 12.9 and 12.7%, respectively.

Exergetic Sustainability Indicators as a Tool in Commercial Aircraft: A Case Study for a Turbofan Engine

This paper focuses on the exergetic sustainability indicators of a medium-range commercial aircraft engine for constant reference environment and ground running conditions. First, a detailed exergy analysis of turbofan engine have been performed based on engine test cell parameters. Starting from the sustainability considerations and the second law of the thermodynamics, the paper presents six exergy-based sustainability indicators. The indicators of the turbofan engine developed here in conjunction with exergetic analysis and sustainable development are exergy efficiency, waste exergy ratio, exergy destruction factor, recoverable exergy rate, environmental effect factor, and exergetic sustainability index. The investigated sustainable indicators have been calculated by using exergy analysis outputs for aircraft ground running condition. Results from this study show that values of exergy efficiency, waste exergy ratio, exergy destruction factor, recoverable exergy rate, environmental effect factor, and exergetic sustainability index of investigated turbofan engine are found to be 0.315, 0.685, 0.408, 0, 2.174, and 0.460, respectively. These parameters are expected to quantify how the turbofan engine and aircraft become more environmentally benign and sustainable.

Exergoeconomic analysis of an aircraft turbofan engine

This study deals with an exergoeconomic analysis of an aircraft turbofan engine utilising the kerosene as fuel. A new parameter is developed to define the thrust cost rate. The cost of exergy destruction, the relative cost difference and the exergoeconomic factor are investigated. The variation of the relative cost difference and exergoeconomic factor according to the operating and maintenance costs and the annual operating hour are also studied. For a high by-pass and high thrust rated engine, the cost rate of thrust is obtained to be 304.35

Energetic and exergetic performance assessment of a turboprop engine at various loads

(hkN) −1 for the hot thrust and 138.96

Sustainability assessment of PW6000 turbofan engine: an exergetic approach

(hkN)−1 for the cold thrust, respectively.

Exergoenvironmental analysis of piston–prop aircrafts

It is necessary to understand the mechanisms that have enabled improvements of performance parameters such as thermodynamics efficiencies, thrust or power, specific fuel consumption and specific power in aero engines, thus reducing environmental impact. In this study, a thermodynamic analysis of a turboprop engine is performed at full and partial load conditions. The maximum overall and exergy efficiencies of the turboprop are found to be 30.7 and 29.2%, respectively. The minimum specific fuel consumption and maximum shaft power are found to be 0.2704 kg (kWh)−1 and 1948 shp at maximum load, respectively. More important, the optimum functional load conditions of the engine are observed at higher loads. The results from this study are expected to assist propeller aero–engine design work, where the first and second laws provide a more comprehensive assessment of performance, allowing the turboprop engine concept to be better tailored to specific types of regional transport aircraft.

Assessment of thermodynamic performance and exergetic sustainability of turboprop engine using mixture of kerosene and methanol

In this paper, theory, methodology and example application are developed and shown for a PW6000 high-bypass turbofan engine in terms of exergo-sustainable perspective. To obtain exergetic sustainability indicators, first, detailed exergy analysis is performed for the engine. The investigated exergetic sustainability indicators are exergy efficiency, waste exergy ratio, exergy destruction factor, environmental effect factor and exergetic sustainability index. These parameters are obtained as 29.7%, 70.3%, 59.4%, 2.367 and 0.423 for the engine at maximum take-off flight condition, respectively. Finally, these parameters are also expected to help understand the linkage between propulsion system design parameters and global aspects in terms of environmental impact and sustainable development and hence make the engine more environmentally benign and more sustainable.

Customised application of exergy analysis method to PW120A turboprop engine for performance evaluation

This study deals with exergoenvironmental analysis of a four–cylinder, spark ignition, naturally aspirated and air–cooled piston–prop aircraft engine for landing takeoff (LTO) and cruise phases. This analysis includes the three steps as follows: application of exergy analysis, finding the exergoenvironmental impacts, and allocation of both exergy streams and exergoenvironmental impacts. In the LTO phase, the maximum specific environmental impact and relative environmental difference is calculated as 18.8 mPts/MJ and 208.9%, respectively, at the approach phase. The maximum specific environmental impact of production is 12.2 mPts/MJ at 3000 m altitude, 15.1 air–to–fuel ratio and 65% rated power setting during the cruise phase.