From the research point of view, it is most interesting to determine both the effect s/g-instrumentation and assembling the compressor stages on blade frequency mistuning. Blade-by-blade impact tests according to a patented approach are used for this purpose. However, it is well known that s/g on blades can contribute additional mistuning that had to be considered upon updating structural models.ĭue to the relevance of mistuning, efforts are made for its accurate experimental determination. To gain the maximum information regarding the correlation between BTT data, s/g-data and pressure gauge data, every blade of the second stage rotor (28 blades) is applied with s/g. Furthermore, these models are required to support the assessment of blade tip timing (BTT) data gathered in the rig tests and strain gauge (s/g) data as well. That is why structural models are needed, allowing for an accurate forced response prediction close to reality. Among others the interaction of aeroelastics and blade mistuning is demanding attention in this regard. The comprehensive test program is addressing both surge and forced response analyses e.g. The analyses are focused on the second rotor of this research compressor, which is the only one being manufactured as blisk. It is planned to achieve trend-setting advances based on a close combination of both numerical and experimental analyses. The superior objective of the research project is to contribute to a reliable but simultaneously less conservative design of future high pressure blade integrated disks (blisk). In order to prepare an advanced 4-stage high-pressure compressor rig test campaign, details regarding both accomplishment and analysis of preliminary experiments are provided in this paper.
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