Performance of a Supercritical CO2 Bottoming Cycle for Aero Applications

Jacob, Florian; Rolt, Andrew; Sebastiampillai, Joshua; Sethi, Vishal; Belmonte, Mathieu; Cobas, Pedro

doi:10.3390/app7030255

Cited by 21 publications

(10 citation statements)

References 17 publications

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“…A big contributor to achieve those targets is the propulsion system. Novel propulsion concepts with intercoolers [2], topping cycles [3] or bottoming cycles [4] are currently under investigation to reduce the specific fuel consumption. Another promising approach seems to be a higher electrification of the on-board systems or even the propulsion system.…”

Section: Introductionmentioning

confidence: 99%

Assessment of Aircraft Surface Heat Exchanger Potential

2019

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Providing sufficient cooling power for an aircraft will become increasingly challenging with the introduction of (hybrid-) electric propulsion. To avoid excessive drag from heat exchangers, the heat sink potential of the aircraft surface is evaluated in this study. Semi-empirical correlations are used to estimate aircraft surface area and heat transfer. The impact of surface heating on aircraft drag is qualitatively assessed. Locating surface heat exchangers where fully turbulent flow is present promises a decrease in aircraft drag. Surface cooling potential is investigated over a range from small regional aircraft to large wide body jets and a range of surface temperatures. Four mission points are considered: Take-off, hot day take-off, climb and cruise. The results show that surface heat exchangers can provide cooling power in the same order of magnitude as the waste heat expected from (hybrid-) electric drive trains for all sizes of considered aircraft. Also, a clear trend favouring smaller aircraft with regards to the ratio of available to required cooling power is visible.

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Section: Introductionmentioning

confidence: 99%

Assessment of Aircraft Surface Heat Exchanger Potential

2019

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“…The aim was to build a standard software tool fulfilling industrial requirements in the area of gas-turbine performance. Further capabilities requested by the tool's industrial and academic users are gradually incorporated by the developers, making PROOSIS a state-of-the-art platform for multi-disciplinary, multi-fidelity and multi-system modeling and simulation of gas turbines [14][15][16][17].…”

Section: Introductionmentioning

confidence: 99%

Novel Aero-Engine Multi-Disciplinary Preliminary Design Optimization Framework Accounting for Dynamic System Operation and Aircraft Mission Performance

et al. 2021

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This paper presents a modular, flexible, extendable and fast-computational framework that implements a multidisciplinary, varying fidelity, multi-system approach for the conceptual and preliminary design of novel aero-engines. In its current status, the framework includes modules for multi-point steady-state engine design, aerodynamic design, engine geometry and weight, aircraft mission analysis, Nitrogen Oxide (NOx) emissions, control system design and integrated controller-engine transient-performance analysis. All the modules have been developed in the same software environment, ensuring consistent and transparent modeling while facilitating code maintainability, extendibility and integration at modeling and simulation levels. Any simulation workflow can be defined by appropriately combining the relevant modules. Different types of analysis can be specified such as sensitivity, design of experiment and optimization. Any combination of engine parameters can be selected as design variables, and multi-disciplinary requirements and constraints at different operating points in the flight envelope can be specified. The framework implementation is exemplified through the optimization of an ultra-high bypass ratio geared turbofan engine with a variable area fan nozzle, for which specific aircraft requirements and technology limits apply. Although the optimum design resulted in double-digit fuel-burn benefits compared to current technology engines, it did not meet engine-response requirements, highlighting the need to include transient-performance assessments as early as possible in the preliminary engine design phase.

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“…Moreover, other aero engine configurations that use different technologies such as the recuperation technology are proposed which are mainly studying the exploitation of the otherwise wasted heat energy at the exhaust nozzle. These configurations are utilizing the increased enthalpy content of the hot gas either to preheat the compressor discharge air 5,6 or to heat another fluid within a secondary fluid system which is used for power generation, 7 typically in a bottoming Rankine thermodynamic cycle.…”

Section: Introductionmentioning

confidence: 99%

Conceptual design study of a geared turbofan and an open rotor aero engine with intercooled recuperated core

Salpingidou

Misirlis

Vlahostergios

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The development of more efficient aero engines is becoming a matter of great importance due to the need for pollutant emissions reduction (e.g. CO 2 , NO x). Toward this direction, two of the most promising aero engine architectures that have been proposed are the ultrahigh bypass geared turbofan and the open rotor configurations, both of which are targeting the low thrust-specific fuel consumption and reduced NO x production. In the current study, investigations are performed in order to determine the improvements in thrust-specific fuel consumption for these configurations. More specifically, on the basic geared turbofan and open rotor configurations an intercooler and a recuperator are implemented between the compressors and the exhaust nozzle, respectively. The intercooler is installed in order to reduce the high pressure compressor work demand, while the recuperator is used in order to preheat the compressor discharge air by exploiting the otherwise wasted increased enthalpy content of the exhaust hot gas. The recuperator consists of elliptically profiled tubes and its design is based on the innovative tubular heat exchanger core arrangement that has been invented and developed by MTU Aero engines AG. The intercooled recuperative geared turbofan is evaluated against a nonintercooled recuperative geared turbofan, while the intercooled recuperative open rotor is evaluated against a nonintercooled recuperative open rotor. The results showed that the implementation of intercoolers and recuperators can further improve specific fuel consumption and can also lead to NO x emission reduction.

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Performance of a Supercritical CO2 Bottoming Cycle for Aero Applications

Cited by 21 publications

References 17 publications

Assessment of Aircraft Surface Heat Exchanger Potential

Assessment of Aircraft Surface Heat Exchanger Potential

Novel Aero-Engine Multi-Disciplinary Preliminary Design Optimization Framework Accounting for Dynamic System Operation and Aircraft Mission Performance

Conceptual design study of a geared turbofan and an open rotor aero engine with intercooled recuperated core

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