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An integrated methodology to assess the operational and environmental performance of a conceptual regenerative helicopter

Published online by Cambridge University Press:  27 January 2016

F. Ali ,
I. Goulos  and
V. Pachidis
F. Ali*
Affiliation:
Propulsion Centre, Propulsion Centre, School of Aerospace, Transport and Manufacturing, Cranfield University, Bedford, UK
I. Goulos
Affiliation:
Propulsion Centre, Propulsion Centre, School of Aerospace, Transport and Manufacturing, Cranfield University, Bedford, UK
V. Pachidis
Affiliation:
Propulsion Centre, Propulsion Centre, School of Aerospace, Transport and Manufacturing, Cranfield University, Bedford, UK
*
f.ali@cranfield.ac.uk
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Abstract

This paper aims to present an integrated multidisciplinary simulation framework, deployed for the comprehensive assessment of combined helicopter–powerplant systems at mission level. Analytical evaluations of existing and conceptual regenerative engine designs are carried out in terms of operational performance and environmental impact. The proposed methodology comprises a wide-range of individual modeling theories applicable to helicopter flight dynamics, gas turbine engine performance as well as a novel, physics-based, stirred reactor model for the rapid estimation of various helicopter emissions species. The overall methodology has been deployed to conduct a preliminary trade-off study for a reference simple cycle and conceptual regenerative twin-engine light helicopter, modeled after the Airbus Helicopters Bo105 configuration, simulated under the representative mission scenarios. Extensive comparisons are carried out and presented for the aforementioned helicopters at both engine and mission level, along with general flight performance charts including the payload-range diagram. The acquired results from the design trade-off study suggest that the conceptual regenerative helicopter can offer significant improvement in the payload-range capability, while simultaneously maintaining the required airworthiness requirements. Furthermore, it has been quantified through the implementation of a representative case study that, while the regenerative configuration can enhance the mission range and payload capabilities of the helicopter, it may have a detrimental effect on the mission emissions inventory, specifically for NOx(Nitrogen Oxides). This may impose a trade-off between the fuel economy and environmental performance of the helicopter. The proposed methodology can effectively be regarded as an enabling technology for the comprehensive assessment of conventional and conceptual helicopter-powerplant systems, in terms of operational performance and environmental impact as well as towards the quantification of their associated trade-offs at mission level.

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1211 , January 2015 , pp. 67 - 90
Copyright
Copyright © Royal Aeronautical Society 2015

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References

1.Sample, R.D. Research requirements for development of regenerative engines for helicopters, NASA technical report, NASA CR-145112.Google Scholar
2. Advisory Council for Aeronautics Research in Europe Report, Strategic Research Agenda, Volume 1, October 2002. Available at: http://ec.europa.eu/research/transport/pdf/acare_strategic _research_en.pdf.Google Scholar
3.Rosen, K.M. A Prospective, The Importance of Propulsion Technology to the Development of Helicopter Systems with a Vision for the Future The 27th Alexander A. Nikolsky Lecture, J American Helicopter Society.Google Scholar
4.Cohen, H.GFC Rogers, HIH Saravanamoutto, 1996, Gas Turbine Theory, 4th ed.Padstow, Cornwall, UK.Google Scholar
5.Ali, F., Goulos, I., Pachidis, V., Mahmood, T. and pilidis, P.Helicopter mission analysis for a recuperated turboshaft engine, Proceedings of ASME Turbo Expo 2013: Power for Land, Sea and Air, 3-7 June 2013, San Antonio, Texas, USA.Google Scholar
6.Kailos, N.C.Increased helicopter capability through advanced power plant technology J American Helicopter Society, 12, (3), pp 1–15.CrossRefGoogle Scholar
7.Privoznik, E.J.Allison T63 Regenerative Program. American Helicopter Society 24th Annual Forum Proceedings, Washington, DC, USA, May 1968.Google Scholar
8.McDonald, C.F.F.Massardo, A.F., Rodgers, C. and Stone, A.Regenerated gas turbine aero-engines, Part I: early development activities, Aircraft Engineering and Aerospace Technology, 2008, 80, (2), pp 139–157.CrossRefGoogle Scholar
9.McDonald, c.F., Massardo, A.F., Rodgers, C. and Stone, A.Regenerated gas turbine aero-engines. Part II: engine design studies following early development testing, Aircraft Engineering and Aerospace Technology, 2008, 80, (3), pp 280–294.CrossRefGoogle Scholar
10.McDonald, C.F. F.Massardo, A.F., Rodgers, C. and Stone, A.Regenerated gas turbine aero-engines. Part III: engine concepts for reduced emissions, lower fuel consumption, and noise abatement, Aircraft Engineering and Aerospace Technology, 2008, 80, (4), pp 408–426.CrossRefGoogle Scholar
11.Hendricks, R.C., Lowery, N., Dagget, D.L. and Anast, P.Future fuel scenarios and their potential impact to aviation NASA Glenn research Center, Cleveland, Ohio, 44135. Report is accessible at http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20070010 628.pdfGoogle Scholar
12.Goulos, I.Simulation Framework Development for the Multidisciplinary Optimization of Rotorcraft, PhD thesis, 2012, Cranfeld University, Cranfeld, Bedfordshire, UK.Google Scholar
13.Goulos, I., Pachidis, V. and Pilidis, P.Lagrangian formulation for the rapid estimation of helicopter rotor blade vibration characteristics, Aeronaut J, August 2014, 118, (1206).CrossRefGoogle Scholar
14. European Organization for the Safety of Air Navigation (EUROCONTROL) and Institute of Geodesy and Navigation (IfEN), 1998, WGS 84 Implementation Manual, Eurocontrol, Brussels, Belgium.Google Scholar
15.Goulos, I., Pachidis, V. and Pilidis, P.Helicopter rotor blade fexibility simulation for aeroelasticity and fight dynamics applications, J Am Helicopter Soc, October 2014, 59, (4).CrossRefGoogle Scholar
16.Goulos, I., Pachidis, V. and Pilidis, P.Real-time aeroelasticity simulation of open rotor with slender blades for the multidisciplinary design of rotorcraft, ASME J Eng. Gas Turbines and Power, January 2015, 137, (1).CrossRefGoogle Scholar
17.MacMillan, W.L.Development of a Module Type Computer Program for the Calculation of Gas Turbine Off Design Performance, PhD thesis, 1974, Cranfeld University, Cranfeld, Bedfordshire, UK.Google Scholar
18.Celis, C.Evaluation and Optimisation of Environmentally Friendly Aircraft Propulsion Systems, 2010, PhD thesis, Cranfeld University, Bedfordshire, UK.Google Scholar
19.Goulos, I., Giannakakis, P., Pachidis, V. and Pilidis, P.Mission performance simulation of integrated helicopter–engine systems using an aeroelastic rotor model, 2013, ASME J Eng, Gas Turbines Power, 135, (9), 091201-1.CrossRefGoogle Scholar
20.Ali, F., Tzanidakis, K., Goulos, I. and Pachidis, V.Multi-objective optimization of conceptual rotorcraft powerplants: trade-off between rotorcraft fuel effciency and environmental impact, ASME J Eng. Gas Turbines Power, 137, (7), 071201, 1 July 2015).Google Scholar
21.Li, Y.G., Marinai, L., Gatto, E.L., Pachidis, V. and Pilidis, P.Multiple-point adaptive performance simulation tuned to aeroengine test-bed data, J Propulsion and Power, 2009, 25, (3), pp 635–641.CrossRefGoogle Scholar
22.Pachidis, V., Pilidis, P., Marinai, L. and Templalexis, I.Towards a full two dimensional gas turbine performance simulator, Aeronaut J, 2007, 111, (1121), pp 433–442.CrossRefGoogle Scholar
23.Goulos, I., Ali, F., Tzanidakis, K., Pachidis, V. and D’ippolito, R.R.A multidisciplinary approach for the comprehensive assessment of integrated rotorcraft–powerplant systems at mission level, ASME J Eng Gas Turbines Power, 137, p 012603-1.Google Scholar
24.Jane’s International Aero-engines, Aircraft Engines of the World, 20, pp 260–261.Google Scholar
25.Gordon, S. and Mcbride, B.J.Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications, 1994, I. Analysis, References 240 NASA Reference Publication 1311, National Aeronautics and Space Administration, Lewis Research Center, Ohio, USA.Google Scholar
26.Celis, C., Long, R., Sethi, V. and Zammit Mangion, D.On Trajectory Optimization for Reducing the Impact of Commercial Aircraft Operations on the Environment, 2009, ISABE-2009 1118, 19th Conference of the International Society for Air Breathing Engines, Montréal, Canada.Google Scholar
27.Fletcher, R.S. and Heywood, J.B.A Model for Nitric Oxide Emissions, from Aircraft Gas Turbine Engines, 1971, AIAA Paper 71-123, AIAA 9th Aerospace Sciences Meeting, New York, USA.CrossRefGoogle Scholar
28.Bowman, C.T.Control of Combustion-Generated Nitrogen Oxide Emissions: Technology Driven by Regulation, 1992, Twenty-Fourth Symposium (International) on Combustion/The Combustion Institute, Sydney, Australia.Google Scholar
29.Miller, J.A. and Bowman, C.T.Mechanism and modelling of nitrogen chemistry in combustion, Progress in Energy and Combustion Science, 1989, 15, pp 287–338.CrossRefGoogle Scholar
30.Marek, C.J. and Tacina, R.R. Effect of exhaust gas recirculation on emissions from a flame tube combustor using liquid jet a fuel NASA technical report, NASA TM X-3464.Google Scholar
31.Rindlisbacher, T., Guidance of the Determination of Helicopter Emissions, Federal Offce of Civil Aviation (FOCA), Division Aviation Policy and Strategy, Reference:0/3/33/33-05-20, 2009.Google Scholar