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Off-design performance analysis of hybridised aircraft gas turbine

Published online by Cambridge University Press:  08 August 2019

X. Zhao Open the ORCID record for X. Zhao [Opens in a new window] ,
S. Sahoo ,
K. Kyprianidis ,
J. Rantzer  and
M. Sielemann
X. Zhao*
Affiliation:
Future Energy Center School of Business, Society and Engineering Mälardalen University Västerås, Sweden
S. Sahoo
Affiliation:
Future Energy Center School of Business, Society and Engineering Mälardalen University Västerås, Sweden
K. Kyprianidis
Affiliation:
Future Energy Center School of Business, Society and Engineering Mälardalen University Västerås, Sweden
J. Rantzer
Affiliation:
Modelon AB Lund, Sweden Modelon Deutschland GmbH München, Germany
M. Sielemann
Affiliation:
Modelon AB Lund, Sweden Modelon Deutschland GmbH München, Germany
*
xin.zhao@mdh.se
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Abstract

An advanced geared turbofan with year 2035 technology level assumptions was established and used for the hybridisation study in this paper. By boosting the low-speed shaft of the turbofan with electrical power through the accessory gearbox, a parallel hybrid concept was set up. Focusing on the off-design performance of the hybridised gas turbine, electrical power input to the shaft, defined as positive hybridisation in this context, generally moves the compressor operation towards surge. On the other hand, the negative hybridisation, which is to reverse the power flow direction can improve the part-load operations of the turbofan and minimise the use of compressor handling bleeds. For the pre-defined mission given in the paper, negative hybridisation of descent, approach and landing, and taxi operations with 580 kW, 240 kW and 650 kW, respectively was found sufficient to keep a minimum compressor surge margin requirement without handling bleed.

Looking at the hybridisation of key operating points, boosting the cruise operation of the baseline geared turbofan is, however, detrimental to the engine efficiency as it is pushing the cruise operation further away from the energy optimal design point. Without major modifications to the engine design, the benefit of the hybridisation appears primarily at the thermomechanical design point, the hot-day take-off. With the constraint of the turbine blade metal temperature in mind, a 500kW positive hybridisation at hot-day take-off gave cruise specific fuel consumption (SFC) reduction up to 0.5%, mainly because of reduced cooling flow requirement. Through the introduction of typical electrical power system performance characteristics and engine performance exchange rates, a first principles assessment is illustrated. By applying the strategies discussed in the paper, a 3% reduction in block fuel burn can be expected, if a higher power density electrical power system can be achieved.

Keywords

Parallel hybridGeared turbofanOff-design performance
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1270 , December 2019 , pp. 1999 - 2018
Copyright
© Royal Aeronautical Society 2019 

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Footnotes

A version of this paper was presented at the 24th ISABE Conference in Canberra, Australia, September 2019.

References

REFERENCES

Strategic Research & Innovation Agenda. 2017 Update |Volume 1, Advisory Council for Aviation Research and Innovation in Europe.Google Scholar
Krein, A. and Williams, G. Flightpath 2050: Europe’s vision for aeronautics, Innovation for Sustainable Aviation in a Global Environment: Proceedings of the Sixth European Aeronautics Days, Madrid, Spain, 2012, p 63.Google Scholar
Kallas, S. and Geoghegan-Quiin, M. Flightpath 2050: Europe’s Vision for Aviation: Report of the High-Level Group on Aviation Research, European Union, 2011.Google Scholar
Bradley, M.K. and Droney, C.K. Subsonic Ultra Green Aircraft Research: Phase I Final Report, National Aeronautics and Space Administration, Langley Research Center, 2011.Google Scholar
Bradley, M.K. and Droney, C.K. Subsonic Ultra Green Aircraft Research: Phase 2. Volume 2; Hybrid Electric Design Exploration, NASA, https://ntrs.nasa.gov, 2015, CR-2015-218704.Google Scholar
Bradley, M. and Droney, C. Subsonic Ultra Green Aircraft Research Phase II: n+ 4 Advanced Concept Development, NASA, https://ntrs.nasa.gov, 2012, CR-2012-217556.Google Scholar
Seitz, A. Advanced Methods for Propulsion System Integration in Aircraft Conceptual Design, PhD dissertation, Technische Universität München, 2012.Google Scholar
SEitz, A., Isikveren, A.T. and Hornung, M. Pre-concept performance investigation of electrically powered aero-propulsion systems, 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, San Jose, California, USA, 2013, p 3608.CrossRefGoogle Scholar
Seitz, A., et al. Electrically Powered Propulsion: Comparison and Contrast to Gas Turbines, Deutsche Gesellschaft für Luft-und Raumfahrt-Lilienthal-Oberth eV, Berlin, Germany, 2012.Google Scholar
Isikveren, A.T., et al. Conceptual studies of universally electric systems architectures suitable for transport aircraft, Deutscher Luft-und Raumfahrt Kongress, DLRK, Berlin, 2012.Google Scholar
Stückl, S., Van Toor, J. and Lobentanzer, H. VOLTAIR – the all-electric propulsion concept platform – a vision for atmospheric friendly flight, 28th International Congress of the Aeronautical Sciences (ICAS), Brisbane, Australia, 2012.Google Scholar
Jansen, R., et al. Overview of NASA Electrified Aircraft Propulsion (EAP) Research for Large Subsonic Transports, 53rd AIAA/SAE/ASEE Joint Propulsion Conference, Atlanta, Georgia, USA, 2017.CrossRefGoogle Scholar
Isikveren, A.T., et al. Pre-design strategies and sizing techniques for dual-energy aircraft, Aircr Eng Aerosp Technol: Int J, 2014, 86, (6), pp 525–542.CrossRefGoogle Scholar
Isikveren, A.T., et al. Conceptual studies of future hybrid-electric regional aircraft, 22nd International Symposium on Air Breathing Engines, Phoenix, Arizona, 2015.Google Scholar
Isikveren, A.T., et al. Optimization of commercial aircraft using battery-based voltaic-joule/Brayton propulsion, J Aircr, 2016, 54, pp 246–261.Google Scholar
Pornet, C., et al. Methodology for sizing and performance assessment of hybrid energy aircraft, J Aircr, 2014, 52, (1), pp 341–352.CrossRefGoogle Scholar
Pornet, C. and Isikveren, A. Conceptual design of hybrid-electric transport aircraft, Prog Aerosp Sci, 2015, 79, pp 114–135.CrossRefGoogle Scholar
Pornet, C., Kaiser, S., and Gologan, C. Cost-based flight technique optimization for hybrid energy aircraft, Aircr Eng Aerosp Technol: Int J, 2014, 86, (6), pp 591–598.Google Scholar
Pornet, C., et al. Integrated fuel-battery hybrid for a narrow-body sized transport aircraft, Aircr Eng Aerosp Technol: Int J, 2014, 86, (6), pp 568–574.Google Scholar
Lents, C.E., et al. Parallel hybrid gas-electric geared turbofan engine conceptual design and benefits analysis, 52nd AIAA/SAE/ASEE Joint Propulsion Conference, American Institute of Aeronautics and Astronautics, Salt Lake City, Utah, USA, 2016.CrossRefGoogle Scholar
Freeh, J.E., Steffen, C.J. and Larosiliere, L.M. Off-design performance analysis of a solid-oxide fuel cell/gas turbine hybrid for auxiliary aerospace power, ASME 2005 3rd International Conference on Fuel Cell Science, Engineering and Technology, American Society of Mechanical Engineers, Ypsilanti, Michigan, USA, 2005.Google Scholar
Lupelli, L. and Geis, T. A Study on the Integration of the IP Power Offtake System Within the Trent 1000 Turbofan Engine, Msc. Thesis, Pisa University, 2012, https://etd.adm.unipi.it.Google Scholar
Kyprianidis, K.G. Multi-Disciplinary Conceptual Design of Future Jet Engine Systems. PhD dissertation, Cranfield University, 2010.Google Scholar
Kyprianidis, K.G. An approach to multi-disciplinary aero engine conceptual design, 23rd International Society for Air Breathing Engines, Manchester, UK, 2017.Google Scholar
Kyprianidis, K.G., et al. EVA: A tool for environmental assessment of novel propulsion cycles, ASME. Turbo Expo: Power for Land, Sea, and Air, Volume 2: Controls, Diagnostics and Instrumentation; Cycle Innovations; Electric Power 2008, (43123), pp 547–556.CrossRefGoogle Scholar
Hwang, J.T. A Modular Approach to Large-Scale Design Optimization of Aerospace Systems, PhD dissertation, University of Michigan, 2015.Google Scholar
Gray, J.S., et al. Automatic evaluation of multidisciplinary derivatives using a graph-based problem formulation in OpenMDAO, 15th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Atlanta, Georgia, USA, 2014.CrossRefGoogle Scholar
Jenkinson, L.R., et al. Civil Jet Aircraft Design, Vol. 338, Arnold, 1999, London.CrossRefGoogle Scholar
Roskam, J. Airplane Design: Part 5-Component Weight Estimation, DARcorporation, 1985, Lawrence, Kansas, USA.Google Scholar
Torenbeek, E. Synthesis of Subsonic Airplane Design: An Introduction to the Preliminary Design of Subsonic General Aviation and Transport Aircraft, with Emphasis on Layout, Aerodynamic Design, Propulsion and Performance, Springer Science & Business Media, 2013, Dordrecht, Netherland.Google Scholar
ESDU, Estimation of airframe drag by summation of components—principles and examples. Engineering Sciences Data Unit, IHS Group, London, UK, 1997. Standard NO. ESDU-97016.Google Scholar
Laskaridis, P. Performance Investigations and Systems Architectures for the More Electric Aircraft. PhD dissertation, Cranfield University, 2004.Google Scholar
Kyprianidis, K.G. and Rolt, A.M. On the optimisation of a geared fan intercooled core engine design, ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, American Society of Mechanical Engineers, Dusseldorf, Germany, 2014.Google Scholar
Kyprianidis, K.G., Rolt, A.M. and Grönstedt, T. Multidisciplinary analysis of a geared fan intercooled core aero engine, J Eng Gas Turbines Power, 2014, 136, (1), p 011203.CrossRefGoogle Scholar
Xu, L., Kyprianidis, K.G. and Grönstedt, T.U.J. Optimization study of an intercooled recuperated aero engine, J Propul Power, 2013, 29, (2), pp 424–432.Google Scholar
Kyprianidis, K.G., et al. Assessment of future aero engine designs with intercooled and inter-cooled recuperated cores, J Eng Gas Turbines Power, 2011, 133, (1), p 011701.Google Scholar
Kyprianidis, K.G. and Dahlquist, E. On the trade-off between aviation NOx and energy efficiency. Appl Energy, 2017, 185, pp 1506–1516.CrossRefGoogle Scholar
FMI Standard, https://fmi-standard.org/, 2018.Google Scholar
Andersson, C., Åkesson, J. and Führer, C. PyFMI: A python package for simulation of coupled dynamic models with the functional mock-up interface. Technical Report in Mathematical Sciences, 2016, p 40.Google Scholar
MODELON, PyFMI, https://pypi.org/project/PyFMI/, 2018.Google Scholar
Saravanamuttoo, H.I.H., et al. Gas Turbine Theory, 6th ed. Prentice Hall, 2009, Harlow, England; New York.Google Scholar
Grieb, H. Projektierung von Turboflugtriebwerken. Technik der Turboflugtriebwerke, Birkhäuser Verlag, 2004, Basel, 826 S.Google Scholar
International Aero Engines (IAE), L., Type Certificate Data Sheets and Specifications for PW1100G-JM Series Engines, Federal Aviation Administration, 2018, US.Google Scholar
Lolis, P. Development of a preliminary weight estimation method for advanced turbofan engines, PhD dissertation, Cranfield University, 2014.Google Scholar
Samuelsson, S., Kyprianidis, K.G. and Grönstedt, T. Consistent conceptual design and performance modeling of aero engines, ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, American Society of Mechanical Engineers, Montreal, Quebec, Canada, 2015.Google Scholar
Airbus, S. Aircraft characteristics airport and maintenance planning, Google Scholar, 2005.Google Scholar
Walsh, P.P. and Fletcher, P. Gas Turbine Performance, John Wiley & Sons, 2004, Oxford, UK.CrossRefGoogle Scholar
Guha, A. Optimum fan pressure ratio for bypass engines with separate or mixed exhaust streams, J Propul Power, 2001, 17, (5), pp 1117–1122.CrossRefGoogle Scholar
Trawick, D., et al. Development and application of GT-HEAT for the electrically variable engine(TM) design, 55th AIAA Aerospace Sciences Meeting, American Institute of Aeronautics and Astronautics, Grapevine, Texas, USA, 2017.Google Scholar
Culley, D.E., Kratz, J.L. and Thomas, G.L. Turbine Electrified Energy Management (TEEM) for enabling more efficient engine designs, 2018 Joint Propulsion Conference, American Institute of Aeronautics and Astronautics, Cincinnati, Ohio, USA, 2018.CrossRefGoogle Scholar
Brelje, B.J. and Martins, J.R.R.A. Electric, hybrid, and turboelectric fixed-wing aircraft: A review of concepts, models, and design approaches, Prog Aerosp Sci, 2019, 104, pp 1–19.Google Scholar
National Academies of Sciences, E. and Medicine. Commercial Aircraft Propulsion and Energy Systems Research: Reducing Global Carbon Emissions, The National Academies Press, 2016, Washington, DC, p 122.Google Scholar
Perullo, C.A., Trawick, D.R. and Mavris, D.N., Assessment of engine and vehicle performance using integrated hybrid-electric propulsion models, J Propul Power, 2016, 32, (6), pp 1305–1314.CrossRefGoogle Scholar
Nagata, H. and Chikusa, Y. All-solid-state lithium-sulfur battery with high energy and power densities at the cell level, Energy Technol, 2016, 4, pp 484–489.Google Scholar
Kyprianidis, K., Future Aero Engine Designs: An Evolving Vision, Intech, 2011, Rijeka, Croatia, pp 3–24.Google Scholar
Kadyk, T., et al. Analysis and design of fuel cell systems for aviation, Energies, 2018, 11, 375.CrossRefGoogle Scholar