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Aerodynamic interaction between the compressor (fan) and the air intake is a characteristic feature of modern turbojet engines of civil aviation. An approach based on unsteady three-dimensional modeling of the flow taking into account full blade rows is necessary for analysis but is too resource-intensive for design. In some cases, an approach based on the “active disk” boundary condition can be successfully used to analyze aerodynamic interference of the engine with airframe elements. In the present work, the flow characteristics in the air intake of a model axial compressor JT8D are studied and different variants of the “active disk” boundary condition that can replace the compressor in the air intake are compared. The results of the computational study of characteristics of the axial compressor model in nacelle based on a pre-validated technique are presented. An analysis of integral characteristics and profiles of variables in different cross-sections at rotational speeds constituting 70, 80 and 90 % of the design value is performed. The results obtained using different variants of the “active disk” boundary condition are compared, and a preferred variant is selected. For the configuration in question, the method has proven to be efficient and accurate.

Computational study of characteristics of intake flow in model axial compressor with regard to different variants of “active disk” boundary condition