The purpose of this paper is to establish a theoretical model to represent a sealed squeeze-film damper bearing and to assess it against results from a test rig, simulating the essential features of a medium-sized gas turbine aero engine.

This paper describes a test facility which reproduces the essential features of a twin-rotor assembly for a medium-size jet engine. Its purpose is to investigate phenomena experienced in an actual engine, which relate to system non-linearities. These phenomena include subharmonics, combination oscillations and jumps in frequency response. All such phenomena manifested themselves in the test facility and explanations are given as to their cause and possible elimination.

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A real design case of an aircraft engine combustor is presented. The design requirements are practical constraints involving thermal, mechanical, and lifing areas. Design optimization of the full combustor structure has been carried out in the federated intelligent product environment. Several enabling technologies have been developed and used, including intelligent master modeling, automated mesh generation, and linked model environment for thermal/mechanical analyses. Whereas the main objective of the project was to introduce the advanced multidisciplinary design analysis/multidisciplinary design optimization technologies to business product development programs, the output of the work served as a design improvement for future modifications.

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