Abstract
Abstract We parameterize the geometry of an industrial aeroengine combustor using Free Form Deformation (FFD). We then define the thermoacoustic system parameters and impose the acoustic boundary conditions to calculate the thermoacoustic eigenmode of the model using an open source parallelized Helmholtz solver. We then use adjoint methods to calculate the shape derivatives of the unstable eigenvalue with respect to the shape parameters. First we calculate the sensitivities with respect to surface movements. Second, we calculate the sensitivities with respect to the FFD control points. We modify the FFD control point positions in order to reduce the thermoacoustic growth rate until the mode considered is stable. These findings show how, when combined with other constraints, this method could be used to reduce combustion instability in industrial annular combustors through geometric modifications.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callSimilar Papers
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
