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Research Papers: Gas Turbines: Aircraft Engine

First and Second Law Analysis of Future Aircraft Engines

[+] Author and Article Information
Tomas Grönstedt

e-mail: tomas.gronstedt@chalmers.se

Oskar Thulin

Chalmers University of Technology,
Gothenburg SE-41296, Sweden

Anders Lundbladh

GKN Aerospace,
Trollhättan SE-46181, Sweden

1Corresponding author.

Contributed by the Aircraft Engine Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 9, 2013; final manuscript received August 7, 2013; published online November 19, 2013. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(3), 031202 (Nov 19, 2013) (10 pages) Paper No: GTP-13-1249; doi: 10.1115/1.4025727 History: Received July 09, 2013; Revised August 07, 2013

An optimal baseline turbofan cycle designed for a performance level expected to be available around year 2050 is established. Detailed performance data are given in take-off, top of climb, and cruise to support the analysis. The losses are analyzed, based on a combined use of the first and second law of thermodynamics, in order to establish a basis for a discussion on future radical engine concepts and to quantify loss levels of very high performance engines. In light of the performance of the future baseline engine, three radical cycles designed to reduce the observed major loss sources are introduced. The combined use of a first and second law analysis of an open rotor engine, an intercooled recuperated engine, and an engine working with a pulse detonation combustion core is presented. In the past, virtually no attention has been paid to the systematic quantification of the irreversibility rates of such radical concepts. Previous research on this topic has concentrated on the analysis of the turbojet and the turbofan engine. In the developed framework, the irreversibility rates are quantified through the calculation of the exergy destruction per unit time. A striking strength of the analysis is that it establishes a common currency for comparing losses originating from very different physical sources of irreversibility. This substantially reduces the complexity of analyzing and comparing losses in aero engines. In particular, the analysis sheds new light on how the intercooled recuperated engine establishes its performance benefits.

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References

Roth, B. A., and Mavris, D. N., 2000, “A Comparison of Thermodynamic Loss Models Suitable for Gas Turbine Propulsion: Theory and Taxonomy,” Joint Propulsion Conference, Huntsville, AL, July 17–19, AIAA Paper No. 2000-3714. [CrossRef]
Goldmeer, J., Tangirala, V., and Dean, A., 2008, “System-Level Performance Estimation of a Pulse Detonation Based Hybrid Engine,” ASME J. Eng. Gas Turbines Power, 130(1), p. 011201. [CrossRef]
Noppel, F., 2011, “Advanced Propulsion Systems for Next Generation Commercial Aircraft,” XXth International Symposium on Air Breathing Engines (ISABE 2011), Gothenburg, Sweden, September 12–16, Paper No. ISABE 2011-1316.
Sciubba, E., and Wall, G., 2007, “A Brief Commented History of Exergy From the Beginnings to 2004,” Int. J. Thermodyn., 10(1), pp. 1–26.
Horlock, J., Young, J. B., and Manfrida, G., 2000, “Exergy Analysis of Modern Fossil-Fuel Power Plants,” ASME J. Eng. Gas Turbines Power, 122(1), pp. 1–7. [CrossRef]
El-Masri, 1985, “On Thermodynamics of Gas-Turbine Cycles—Part 1: Second Law Analysis of Combined Cycles,” ASME J. Eng. Gas Turbines Power, 107(4), pp. 880–889. [CrossRef]
Horlock, J., and Clarke, C., 1975, “Availability and Propulsion,” J. Mech. Eng. Sci., 17(4), pp. 223–232. [CrossRef]
Evans, R. B., 1969, “A Proof That Essergy is the Only Consistent Measure of Potential Work,” Ph.D. thesis, Dartmouth College, Hanover, NH.
Brilliant, H. M., 1995, “Second Law Analysis of Present and Future Turbine Engines,” 31st AIAA/ASME/SAE/ASEE Joint Propulsion Conference, San Diego, CA, July 10–12, AIAA Paper No. 95-3030. [CrossRef]
Rosen, M. A., 2009, “Exergy Losses for Aerospace Engines: Effect of Reference Environment on Assessment of Accuracy,” Int. J. Exergy, 6(3), pp. 405–421. [CrossRef]
Kotas, T. J., 1985, The Exergy Method of Thermal Plant Analysis, Butterworths, London.
Camberos, J. A., and Moorhouse, D. J., 2011, Exergy Analysis and Design Optimization for Aerospace Vehicles and Systems, Prentice-Hall, Englewood Cliffs, NJ.
Engerberg, D., and Thulin, O., 2012, “Aero Engine Exergy Analysis,” Master's thesis, Chalmers University of Technology, Gothenburg, Sweden.
Grönstedt, T., 2012, Propulsion Systems Modeling ( von Karman Institute Lecture Series on Physics-Based Modeling and Simulation for Aerospace Systems), von Karman Institute for Fluid Dynamics, Rhode Saint Genése, Belgium.
Avellan, R., 2011, “On the Design of Energy Efficient Aero Engines—Some Recent Innovations,” Ph.D. thesis, Chalmers University of Technology, Gothenburg, Sweden.
Group of Personalities, 2001, “European Aeronautics: A Vision for 2020,” Office for Official Publications of the European Communities, Luxembourg.
The High Level Group on Aviation Research, 2011, “Flightpath 2050 Europe's Vision for Aviation,” Publications Office of the European Union, Luxembourg.
Avellan, R., and Grönstedt, T., 2007, “Preliminary Design of Subsonic Transport Aircraft Engines,” Paper No. ISABE 2007-1195.
Roskam, J., 2006, “Airplane Design: Part I-VIII,” DARcorporation, Lawrence, KS.
Torenbeek, E., 1982, Synthesis of Subsonic Airplane Design. Delft University Press, Rotterdam, The Netherlands.
IHS ESDU, 1994, “ESDU 81024: Drag of Axisymmetric Cowls at Zero Incidence for Subsonic Mach Numbers,” (amendment), IHS Inc., Englewood, CO.
Lee, J. J., Lukachko, S. P., Waitz, I. A., and Schafer, A., 2001, “Historical and Future Trends in Aircraft Performance, Cost, and Emissions,” Annu. Rev. Energy Environ., 26, pp. 167–200. [CrossRef]
Wilcock, R. C., Young, J. B., and Horlock, J. H., 2005, “The Effect of Turbine Blade Cooling on the Cycle Efficiency of Gas Turbine Power Cycles,” ASME J. Eng. Gas Turbines Power, 127, pp. 109–120. [CrossRef]
Grönstedt, T., 2001, “Development of Methods for Analysis and Optimization of Complex Jet Engine Systems,” Ph.D. thesis, Chalmers University of Technology, Gothenburg, Sweden.
Grieb, H., 2004, Projektierung von Turboflugtriebwerken. Birkhäuser-Verlag, Basel, Switzerland.
Dickens, T., and Day, I., 2011, “The Design of Highly Loaded Axial Compressors,” ASME J. Turbomach., 133(3), p. 031007. [CrossRef]
Tong, M., Halliwell, I., and Ghosn, L., 2004, “A Computer Code for Gas Turbine Engine Weight and Disk Life Estimation,” ASME J. Eng. Gas Turbines Power, 126(2), pp. 265–270. [CrossRef]
Korsia, J. J., and Guy, S., 2007, “VITAL European R&D Programme for Greener Aero-Engines,” Paper No. ISABE 2007-1118.
Kyprianidis, K., Dax, A., Ogaji, S. O. T., and Grönstedt, T., 2009, “Low Pressure System Component Advancements and Its Impact on Future Turbofan Engine Emissions,” Paper No. ISABE-2009-1276.
Larsson, L., Grönstedt, T., and Kyprianidis, K. G., 2007, “Conceptual Design and Mission Analysis for a Geared Turbofan and an Open Rotor Configuration,” ASME Paper No. GT2011-46451. [CrossRef]
McDonald, C., Massardo, A., Rodgers, C., and Stone, A., 2008, “Recuperated Gas Turbine Aeroengines, Part I: Early Development Activites,” Int J. Aircr. Eng. Aerosp. Technol.: 80(2), pp. 139–157. [CrossRef]
Boggia, S., and Rüd, K., 2005, “Intercooled Recuperated Gas Turbine Engine Concept,” AIAA Paper No. 2005-4192. [CrossRef]
Xu, L., 2012, “Analysis and Evaluation of Innovative Aero Engine Core Concepts,” Ph.D. thesis, Chalmers University of Technology, Gothenburg, Sweden.
Kyprianidis, K., Grönstedt, T., Ogaji, S. O. T., Pilidis, P., and Singh, R., 2011, “Assessment of Future Aero-Engine Designs With Intercooled and Intercooled Recuperated Cores,” ASME J. Eng. Gas Turbines Power, 133(1), p. 011701. [CrossRef]
Xu, L., and Grönstedt, T., 2010, “Design and Analysis of an Intercooled Turbofan Engine,” ASME J. Eng. Gas Turbines and Power, 132(11), p. 114503. [CrossRef]
Wainauski, H., Rohrbach, C., and Wynosky, T. A., 1987, “Full Scale Technology Demonstration of a Modern Counterrotating Unducted Fan Engine Concept, Design Report,” NASA Technical Report No. NASA CR-180867.
“Clean Sky: Innovating Together, Flying Greener,” 2013, Clean Sky Joint Undertaking, Brussels, Belgium, http://www.cleansky.eu
Hendricks, S. H., 2011, “Development of an Open Rotor Cycle Model in NPSS Using a Multi-Design Point Approach,” ASME Paper No. GT2011-46649. [CrossRef]
Wintenberger, E., 2004, “Application of Steady and Unsteady Detonation Waves to Propulsion,” Ph.D. thesis, California Institute of Technology, Pasadena, CA.
Wilfert, G., Sieber, J., Rolt, A., and Baker, N., 2007, “New Environmental Friendly Aero Engine Core Concepts,” Paper No. ISABE 2007-1120.
Irannezhad, M., Grönstedt, T., and Eriksson, L.-E., 2011, “Limitations on Tube Filling in a Pulsed Detonation Engine,” Paper No. ISABE 2011-1501.
Irannezhad, M., 2012, “A Numerical Study of Reacting Flow Using Finite Rate Chemistry,” Ph.D. thesis, Chalmers University of Technology, Gothenburg, Sweden.
Paxson, D. E., 1992, “A General Numerical Model for Wave Rotor Analysis,” NASA Technical Report No. TM-105740.

Figures

Grahic Jump Location
Fig. 1

Exergy balance applied to a moving system

Grahic Jump Location
Fig. 2

SFC development trends [15]

Grahic Jump Location
Fig. 3

A schematic overview of the intercooled recuperated concept [33]. The abbreviations used are: IC = intercooler, REC = recuperator, and VGV = variable low pressure turbine guide vane.

Grahic Jump Location
Fig. 4

The open rotor engine (image: Chalmers University)

Grahic Jump Location
Fig. 5

Conceptual illustration of a pulse detonation core (image: Chalmers University)

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