Coherence-based source analysis techniques can be used to identify the contribution of combustion noise in the exhaust of a jet engine and to hence enable the design of noise-reduction devices. However, when the combustion noise propagates in a nonlinear fashion, the identified contribution using ordinary coherence methods will be inaccurate. In this paper, an analysis technique is reported that enables the contribution of linear and nonlinear mechanisms to the propagated sound to be identified. An experimental rig is described for studying the propagation ofnoisethrougharotor/statorsetupusingavaneaxialfanmountedinaductsothatnonlinearinteractionsbetweena soundsourceandthefancanbeinvestigated.Thereportedtechniqueisusedtoidentifyanonlineartonegeneratedby the interaction of the rotor and a propagated tone. The identification procedures are then applied to data from fullscaleturbofanengine testsinstrumentedwith pressuretransducers at thecombustor canandinthehot-jet pipewith microphones in the near field. At a particular power setting, the interaction between the combustion noise and the high-pressure turbine is measured in the hot-jet pipe. The analysis techniques enable nonlinear interactions to be identified and enable linear and nonlinear coherent output powers to be determined.