Hostname: page-component-78c5997874-fbnjt Total loading time: 0 Render date: 2024-11-03T01:36:24.468Z Has data issue: false hasContentIssue false
  • English
  • Français

Multi-objective optimisation of semi-closed cycle engines for high-altitude UAV propulsion

Published online by Cambridge University Press:  07 August 2019

J. Tacconi ,
W. P. J. Visser  and
D. Verstraete Open the ORCID record for D. Verstraete [Opens in a new window]
J. Tacconi*
Affiliation:
School of Aerospace Engineering, Propulsion and Power Delft University of TechnologyDelft, The Netherlands
W. P. J. Visser*
Affiliation:
School of Aerospace Engineering, Propulsion and Power Delft University of TechnologyDelft, The Netherlands
D. Verstraete*
Affiliation:
School of Aerospace, Mechanical and Mechatronic Engineering The University of Sydney, Sydney, Australia
*
[email protected]
[email protected]
[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

The maximum attainable performance of small gas turbines represents a strong limitation to the operating altitude and endurance of high-altitude unmanned aerial vehicles (UAVs). Significant improvement of the cycle thermal efficiency can be achieved through the introduction of heat exchangers, with the consequent increase of the overall engine weight. Since semi-closed cycle engines can achieve a superior degree of compactness compared to their open cycle counterparts, their use can offset the additional weight of the heat exchangers. This paper applies semi-closed cycles to a high-altitude UAV propulsion system, with the objective of assessing the benefits introduced on the engine performance and weight. A detailed model has been created to account for component performance and size variation as function of thermodynamic parameters. The sizing has been coupled with a multi-objective optimisation algorithm for minimum specific fuel consumption and weight. Results of two different semi-closed cycle configurations are compared with equivalent state-of-the-art open cycles, represented by a recuperated and an intercooled-recuperated engine. The results show that, for a fixed design power output, engine weight is approximately halved compared to state-of-the-art open cycles, with slightly improved specific fuel consumption performance. Optimum semi-closed cycles furthermore operate at higher overall pressure ratios than open cycles and make use of recuperators with higher effectiveness as the mass penalty of the recuperator is smaller due to the lower engine mass flow rates.

Keywords

Semi-closed cycleUAV propulsionOptimisation
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1270 , December 2019 , pp. 1938 - 1958
Copyright
© Royal Aeronautical Society 2019 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Footnotes

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

References

REFERENCES

McDonald, C.F. Heat recovery exchangers technology for very small gas turbines, International Journal of Turbo and Jet Engines, 1996, 13, (4), pp 239–261.CrossRefGoogle Scholar
McDonald, C.F. Low-cost compact primary surface recuperator concept for microturbines, Applied Thermal Engineering, 2000, 20, (5), pp 471–497.CrossRefGoogle Scholar
McDonald, C.F. Recuperator considerations for future higher efficiency microturbines, Applied Thermal Engineering, 2003, 23, pp 1463–1487.CrossRefGoogle Scholar
Gasparovic, N. The advantage of semi-closed cycle gas turbines for naval ship propulsion, Naval Engineers Journal, 1968, 80, (2).CrossRefGoogle Scholar
Dewitt, S.H. and Boyum, W.B. Internally fired semi-closed cycle gas turbine plant for naval propulsion. Gas Turbine Power Conference, ASME, 1956.Google Scholar
Lear, W.E. and Laganelli, A.L. High Pressure Regenerative Turbine Engine: 21st Century Propulsion. Tech Rep, NASA Glenn Research Center, 2001.Google Scholar
Meitner, P.L., Laganelli, A.L., Senick, P.F. and Lear, W.E. Demonstration of a Semi-Closed Cycle, Turboshaft Gas Turbine Engine, 2000.Google Scholar
Laganelli, A.L., Rodgers, C., Lear, W.E. and Meitner, P.L. Semi-closed gas turbine cycles: an ecological solution. ASME TURBO EXPO 2001, New Orleans, Louisiana, USA. NASA Glenn Research Center, ASME, 2001.Google Scholar
Bettner, J.L., Blandford, C.S. and Rezy, V. Propulsion System Assessment for Very High Altitude UAV Under ERAST. Tech Rep, Allison Engine Company, Indianapolis, IN, USA, 1995.Google Scholar
Tacconi, J. Investigation of a semi-closed cycle small gas turbine for high altitude UAV propulsion, M.Sc. Thesis, Delft University of Technology, 2018.Google Scholar
Tacconi, J., Visser, W., MacNeill, R. and Verstraete, D. Development of a multi-objective optimization tool for intercooled/recuperated turboprop engines for minimum SFC and engine weight, Proceedings of the 2018 Joint Propulsion and Energy Forum, 2018, pp 1–22. doi: doi.org/10.2514/6.2018-4656Google Scholar
Kumar, G.N. and DeAnna, R.G. Development of a thermal and structural analysis procedure for cooled radial turbines. 33rd International Gas Turbine and Aeroengine Congress and Exposition, Amsterdam, The Netherlands, ASME, 1988.Google Scholar
Horlock, J.H., Watson, D.T. and Jones, T.V. Limitations on gas turbine performance imposed by large turbine cooling flows, Journal of Engineering for Gas Turbines and Power, 2001, 123, (3), pp 487.Google Scholar
Whitfield, A. and Baines, N.C. Design of Radial Turbomachines, Pearson Education, 1990.Google Scholar
Whitfield, A. Preliminary design and performance prediction techniques for centrifugal compressors, Proceedings of the Institution of Mechanical Engineers, 1990, 204, (1), pp 131–144.Google Scholar
Galvas, M.R. Analytical Correlation of Centrifugal Compressor Design Geometry for Maximum Efficiency with Specific Speed, Tech Rep, NASA Lewis Research Center, Cleveland, OH, USA, 1972.Google Scholar
Kim, Y., Engeda, A., Aungier, R. and Amineni, N. A centrifugal compressor stage with wide ow range vaned diffusers and different inlet configurations, Journal Power and Energy, 2002, 216, pp 307–320.CrossRefGoogle Scholar
Galvas, M.R. Fortran Program for Predicting Off-Design Performance of Centrifugal Compressors, Tech Rep, NASA Lewis Research Center and U.S. Army Air Mobility R&D Laboratory, Cleveland, OH, USA, 1973.Google Scholar
Oh, H.W., Yoon, E.S. and Chung, M.K. An optimum set of loss models for performance prediction of centrifugal compressors, Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 1997, 211, (4), pp 331–338.Google Scholar
Aungier, R.H. Mean streamline aerodynamic performance analysis of centrifugal compressors, Journal of Turbomachinery, 1995, 117, pp 360–366.CrossRefGoogle Scholar
Aungier, R.H. Centrifugal Compressors A Strategy for Aerodynamic Design and Analysis. ASME, 2000.CrossRefGoogle Scholar
Harley, P., Spence, S., Early, J., Filsinger, D. and Dietrich, M. An evaluation of 1D loss model collections for the off-design performance prediction of automotive turbocharger compressors. 6th International Conference on Pumps and Fans with Compressors and Wind Turbines. IOP, 2013.CrossRefGoogle Scholar
Rodgers, C. Impeller stalling as influenced by diffusion limitations, Journal of Fluids Engineering, 1977, pp 84–93.CrossRefGoogle Scholar
Whitfield, A. The preliminary design of radial inflow turbines, Journal of Turbomachinery, 1989, 112, (1), pp 50–57.CrossRefGoogle Scholar
Rohlik, H.E. Analytical Determination of Radial Inflow Turbines Design Geometry for Maximum Efficiency, Tech Rep, NASA Lewis Research Center, Cleveland, OH, USA, 1968.Google Scholar
Glassman, A.J. Turbine Design and Application (3 volumes). National Aeronautical and Space Administration, Washington D.C., USA, 1973.Google Scholar
Glassman, A.J. Computer Program for Design Analysis of Radial-Inflow Turbines. Tech Rep, NASA Lewis Research Center, Cleveland, OH, USA, 1976.Google Scholar
Wasserbauer, C.A. and Glassman, A.J. Fortran Program for Predicting Off-Design Performance of Radial-Inflow Turbines. Tech Rep, NASA Lewis Resedrcb Center, Cleveland, OH, USA, 1975.Google Scholar
Baines, N.C. A meanline prediction method for radial turbine efficiency. Sixth International Conference on Turbocharging and Air Management Systems, vol. 1998, pp 45–56, 1998.Google Scholar
Melconian, J.O. and Modak, A.T. Combustor Design, in Sawyer’s Gas Turbine Engineering Handbook, Turbomachinery International Publications, vol. 1, 1985.Google Scholar
Kowaiski, E.J. and Atkins, R.A. A Computer Code for Estimating Installed Performance of Aircraft Gas Turbine Engines. Tech Rep, Advanced Airplane Branch Boeing Military Airplane Company, Seattle, Washington, USA, 1979.Google Scholar
Schutte, J.S. Simultaneous Multi-Design Point Approach to Gas Turbine On-Design Cycle Analysis for Aircraft Engines. Ph.D. thesis, Georgia Institute of Technology, 2009.Google Scholar
Walsh, P.P. and Fletcher, P. Gas Turbine Performance, Blackwell, second edition, 2004.Google Scholar
Zafer, L. An Investigation into Performance Modeling of a Small Gas Turbine Engine, Tech Rep, Australian Government Department of Defence, 2012.Google Scholar
Yoshinaka, T., Thompson, R.G. and Letourneau, J. The performance prediction and demonstration of a centrifugal compressor for the multiple purpose small power unit (MPSPU), Gas Turbine and Aeroengine Congress and Exposition, Totonto, Ontario, Canada, ASME, 1989.Google Scholar
Pullen, K.R. Baines, N.C. and Hill, S.H. The design and evaluation of a high pressure ratio radial turbine, International Gas Turbine & Aeroengine Congress & Exhibition, Cologne, Germany. ASME, 1992, pp 1–7.Google Scholar
Onat, E. and Klees, W.G. A Method to Estimate Weight and Dimensions of Large and Small Gas Turbine Engines, Tech Rep, NASA Lewis Research Center, 1979.Google Scholar
Hale, P.L. A Method to Estimate Weight and Dimensions of Small Aircraft Propulsion Gas Turbine Engines, Tech Rep, NASA Lewis Research Center, 1982.Google Scholar
Rodgers, C. Thermodynamic and Economic Trade Studies for a 3000 kW Gas Turbine, ASME COGEN, 1995.Google Scholar
Head, A.J. and Visser, W.P.J. Scaling 3–36 kW microturbines. ASME TURBO EXPO, Copenhagen, Denmark, ASME, 2012, pp 1–9.Google Scholar
Rodgers, C. 300 kW class, semi-closed cycle gas turbine engine design considerations, International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, IN, USA. ASME, 1999.Google Scholar
Rodgers, C. A cycle analysis technique for small gas turbines, Proceedings of the Institution of Mechanical Engineers, 1969, 183, pp 37–49.Google Scholar
Rejman, E and Rejman, M. Gears weight equation – gear chain weight calculation methodology. MTMVirtual Journals, 2011, (2), pp 18–21.Google Scholar
Dudley, D.W. Handbook of Practical Gear Desing, Technomic Publishing Co., 1994.Google Scholar
Messac, A. Optimization in Practice with MATLAB®: For Engineering Students and Professionals, Cambridge University Press, 2015.CrossRefGoogle Scholar
Deb, K. Multi-Objective Optimization Using Evolutionary Algorithms, John Wiley & Sons, 2001.Google Scholar
Tameo, R.W., Vinson, P.W. and Neitzel, R.E. Regenerative Engine Analysis, Tech Rep, General Electric Company, 1980.Google Scholar
McDonald, C.F. Study of a Lightweight Integral Regenerative Gas Turbine for High Performance, Tech Rep, The Garret Corporation AiResearch Manufacturing Company, Los Angeles, CA, USA, 1970.Google Scholar
Hendricks, E.S. Development of an Open Rotor Cycle Model in NPSS Using a Multi-Design Point Approach, Tech Rep, NASA Glenn Research Center, Cleveland, OH, USA, 2011.Google Scholar
Storn, R. On the Usage of Differential Evolution for Function Optimization, 1996.Google Scholar