Boundary conditions for the computation of thermo-acoustic modes in combustion chambers

Abstract : In order to carry out reliable LES or Helmholtz solver computations in aeronautical combustion chambers, it is crucial to impose the right boundary conditions at both 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 where the boundary condition were derived from the isentropic and isenthalpic Linearized Euler Equations. Specific terms are added to the quasi-1D LEE 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 entropyacoustic coupling since, 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.
Complete list of metadatas

Cited literature [36 references]  Display  Hide  Download

https://hal.archives-ouvertes.fr/hal-01056693
Contributor : Franck Nicoud <>
Submitted on : Wednesday, August 20, 2014 - 1:06:36 PM
Last modification on : Tuesday, September 17, 2019 - 11:02:04 AM
Long-term archiving on : Thursday, November 27, 2014 - 11:51:33 AM

File

AIAA_silva.pdf
Files produced by the author(s)

Identifiers

Citation

Camilo Silva, Ignacio Duran, Franck Nicoud, Stéphane Moreau. Boundary conditions for the computation of thermo-acoustic modes in combustion chambers. AIAA Journal, American Institute of Aeronautics and Astronautics, 2014, 52 (6), pp.1180-1193. ⟨10.2514/1.J052114⟩. ⟨hal-01056693⟩

Share

Metrics

Record views

250

Files downloads

1209