Advertisement

On Thermodynamic Cycles for Detonation Engines

  • R. Vutthivithayarak
  • E. M. Braun
  • F. K. Lu

Introduction

Detonation engines are considered to potentially yield better performance than existing turbo-engines in terms of improved thermodynamic efficiency, simplicity of manufacture and operation, and high thrust-to-weight or thrust-to-volume ratio, amongst other advantages. Much effort has been put into the development of pulsed detonation engines (PDEs), including thermodynamic cycle analysis. Thermodynamic analysis of PDEs usually makes use of one-dimensional models, based on the Chapman–Jouguet (CJ) and the Zeldovich–von Neumann–Döring (ZND) theories, although increasingly sophisticated techniques, some involving numerical modeling, have also been developed lately. It is now understood that the Humphrey cycle used to model an isochoric cycle underpredicts the performance of a PDE [1]–[4]. The so-called Fickett–Jacobs (FJ) cycle is based on the CJ model. While an improvement over the Humphrey cycle, its reliance on the CJ model means that it fails to account for the physics espoused by the ZND model [1, 2]. In this paper, a discussion of the Humphrey and FJ cycles is given and the proper ZND cycle is suggested. These cycles are illustrated with a hydrogen/air mixture initially at STP. The use of a generic heat release parameter to construct the ZND cycle is provided.

Keywords

Detonation Wave Shock Compression Exergy Analysis Thermodynamic Cycle Detonation Process 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. 1.
    Mattingly, J.D.: Elements of Propulsion: Gas Turbines and Rockets. AIAA, Reston (2006)Google Scholar
  2. 2.
    Heiser, W.H., Pratt, D.T.: Thermodynamic Cycle Analysis of Pulse Detonation Engines. J. Propul. Power 18(1), 68–76 (2002)CrossRefGoogle Scholar
  3. 3.
    Kentfield, J.A.C.: Fundamentals of Idealized Airbreathing Pulse-Detonation Engines. J. Propul. Power 18(1), 77–83 (2002)CrossRefGoogle Scholar
  4. 4.
    Wu, Y., Ma, F., Yang, V.: System Performance and Thermodynamic Cycle Analysis of Airbreathing Pulse Detonation Engines. J. Propul. Power 18(4), 556–567 (2003)CrossRefGoogle Scholar
  5. 5.
    Gordon, S., McBride, B.J. (1994), Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications. I. Analysis. NASA RP-1311, http://cea.grc.nasa.gov/
  6. 6.
    Humphrey, H.A.: An Internal-Combustion Pump, and Other Applications of a New Principle. Proc. Inst. Mech. Eng. 77(1), 1075–1200 (1909)CrossRefGoogle Scholar
  7. 7.
    Bussing, T.R.A., Pappas, G.: Pulse Detonation Engine Theory and Concepts. In: Murthy, S.N.B., Curran, E.T. (eds.) Developments in High-Speed Vehicle Propulsion Systems, pp. 421–472. AIAA, Reston (1996)Google Scholar
  8. 8.
    Eidelman, S., Yang, X.: Analysis of the Pulse Detonation Engine Efficiency. AIAA Paper 98–3877 (1998)Google Scholar
  9. 9.
    Hutchins, T.E., Metghalchi, M.: Energy and Exergy Analyses of the Pulse Detonation Engine. J. Eng. Gas Turbines Power 125(4), 1075–1080 (2002)CrossRefGoogle Scholar
  10. 10.
    Talley, D.G., Coy, E.B.: Constant Volume Limit of Pulsed Propulsion for a Constant Gamma Ideal Gas. J. Propul. Power 18(2), 400–406 (2002)CrossRefGoogle Scholar
  11. 11.
    Harris, P.G., Stowe, R.A., Ripley, R.C., Guzik, S.M.: Pulse Detonation Engine as a Ramjet Replacement. J. Propul. Power 22(2), 462–473 (2006)CrossRefGoogle Scholar
  12. 12.
    Wintenberger, E., Shepherd, J.E.: Model for the Performance of Airbreathing Pulse-Detonation Engines. J. Propul. Power 22(3), 593–603 (2006)CrossRefGoogle Scholar
  13. 13.
    Bellini, R., Lu, F.K.: Exergy Analysis of a Pulse Detonation Power Device. J. Propul. Power 26(4), 875–878 (2010)CrossRefGoogle Scholar
  14. 14.
    Li, J.L., Fan, W., Wang, Y.Q., Qiu, H., Yan, C.J.: Performance Analysis of the Pulse Detonation Rocket Engine Based on Constant Volume Cycle Model. Appl. Thermal Eng. 30(11-12), 1496–1504 (2010)CrossRefGoogle Scholar
  15. 15.
    Rao, S.: Effect of Friction on the Zel’dovich–von Neumann–Döring to Chapman–Jouguet Transition. MSAE thesis, Univ Texas Arlington (2010)Google Scholar
  16. 16.
    Vutthivithayarak, R.: Analysis of Pulse Detonation Turbojet Engines. Ph.D. dissertation, Univ Texas Arlington (2011)Google Scholar
  17. 17.
    Goodwin, D.: Cantera: Object-Oriented Software for Reacting Flows (2010), http://code.google.com/p/cantera/

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • R. Vutthivithayarak
    • 1
  • E. M. Braun
    • 1
  • F. K. Lu
    • 1
  1. 1.Aerodynamics Research Center, Mechanical and Aerospace Engineering DepartmentUniversity of Texas at ArlingtonArlingtonUSA

Personalised recommendations