This paper presents analytical linearization schemes of a reduced order aero-thermodynamic model of the generic back end of a turbofan engine. The proposed linearization scheme has advantages of flexibility and reusability over the commonly used linearization method based on the numerical perturbation scheme. Also, a blending algorithm employing the distance to the boundary as the weight has been incorporated into the linearization scheme to capture the change of the flow behaviour near bifurcating boundaries. The proposed linearization scheme is developed and applied to a back end model of a generic turbofan engine with bifurcations corresponding to choked/unchoked boundaries. This model is also used for proof of concept validation test.

This content is only available via PDF.
You do not currently have access to this content.