In order to carry out reliable large-eddy simulation or Helmholtz solver computations in aeronautical combustion chambers, it is crucial to impose the right boundary conditions at both the inlet and outlet of the combustion system. This means providing acoustic boundary impedances that take into account all the stages in compressors and turbines. This study is a follow up of works in which the boundary conditions were derived from the isentropic and isenthalpic linearized Euler equations. Specific terms are added to the quasi-one-dimensional linearized Euler equation in order to account for enthalpy jumps induced by the rotor stages of the compressors and turbines. This system of equations also accounts for the entropy–acoustic coupling because, in addition to the continuity and momentum equations, the entropy equation is also considered. The numerical implementation is validated by comparing the numerical results with analytical solutions in several model problems. The effective impedance of the inlet air circuit of an actual helicopter engine is then computed in order to illustrate the potential of the method as well as the importance of the rotor terms added.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Boundary Conditions for the Computation of Thermoacoustic Modes in Combustion Chambers


    Beteiligte:
    Silva, Camilo F. (Autor:in) / Durán, Ignacio (Autor:in) / Nicoud, Franck (Autor:in) / Moreau, Stéphane (Autor:in)

    Erschienen in:

    AIAA Journal ; 52 , 6 ; 1180-1193


    Erscheinungsdatum :

    2014-02-28


    Format / Umfang :

    14 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch