Onder Turan

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.

Effect of reference altitudes for a turbofan engine with the aid of specific–exergy based method

This paper presents effect of reference altitudes on the exergetic efficiency of a engine with the aid of specific exergy method. between 4000–9000 m. In the analysis, and exergy efficiency of the engine is found to be from 50.34% at 4000 m to 48.91% at 9000 m. Results of this study show that increase in reference altitude decreases the exergy efficiency and increases the energy efficiency of the engine. Additionally, specific exergy analysis can also be used as an integrated indicator for determining the exergetic efficiency.

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.

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

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.

Sustainability assessment of PW6000 turbofan engine: an exergetic approach

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

In this paper, first and second laws of thermodynamics are applied on a turboprop engine of a regional aircraft. Performance parameters of the engine are assessed under take-off conditions and maximum power settings. Energy and exergy rates, exergy destruction rate, improvement potential, fuel depletion rate and productivity rate are proven by using component-based analysis method. Exergy destruction rates are found to be 337.12 kW, 1461.87 kW, 69.74 kW and 269.22 kW in order of air compressor, combustion chamber, gas turbine and free turbine. In addition, exergy efficiencies of the air compressor, combustion chamber, gas turbine and free turbine are calculated to be 86.95%, 82.16%, 97.86% and 85.52%, respectively, whilst energy and exergy efficiencies of the engine are found to be with the values of 27.89% and 26.74%. Obtained results from this study can be useful to improve performance of a turboprop engine still in service.

Exergy analysis of an air-blasted combustor: an application for atmospheric test rig condition

Combustion of fuel finds its importance in heating, power production and transportation. The main objective of this study is to assess the performance of an air-blasted combustor using the exergy at different combustor exit temperatures (T4). Exergetic metrics of the combustor in a test rig were made between 1,100 < T4 ≤ 1500K. JP8 kerosene-type fuel was used for analysis. For the combustor, exergy efficiency was calculated to be between 49.3% and 59.4%. Furthermore, greatest exergy destruction is found at highest combustor exit temperature (138.7 kW at 1500 K), while the lower exergy destructions are found at 1102 K with the value of 90.7 kW. The methodology and the results of this study can be beneficial for further improvement, and development of similar combustor systems for designers.

Exergetic and Energetic Response Surfaces for Small Turbojet Engine

Exergy analysis permits meaningful efficiencies to be evaluated for a system or process, and the sources, causes and locations of thermodynamic losses to be determined. This study presents exergetic modeling of a small turbojet engine via exergetic response surfaces. Turbojet engine consists of an inlet, a centrifugal compressor, reverse flow combustion chamber, axial-flow turbine and exhaust nozzle. The flight Mach number and altitude are examined on the exergetic efficiencies of total engine performance. The results of analysis are given as three dimensional exergetic response surface plots related to these operating parameters.

Effects of Fuel Consumption of Commercial Turbofans on Global Warming

The main objective of this study is to parametrically investigate the fuel consumption effect of commercial turbofans on global warming. In this regard, of the important parameters, specific fuel consumption of commercial turbofans is taken into consideration. In order to minimize the effect of fuel consumption on global warming, the values of engine design parameters are optimized for maintaining minimum specific fuel consumption (SFC*, g/kN s) of high-bypass turbofan engine under different flight conditions and design criteria. The backbones of optimization approach consisted of elitism-based genetic algorithm coupled with real parametric cycle analysis of a turbofan engine. For solving optimization problem a new software program is developed in MATLAB, while objective function is determined for minimizing the specific fuel consumption by considering parameters such as the fan pressure ratio (π f ), bypass ratio (α), and the fuel heating value [h PR (kJ/kg)].