The design of the transonic stages, which form the front two stages of a multi stage compressor, is described. The first stage tip Mach No. is 1.1.

The test programme to evaluate the performance of the two stages is outlined and detailed results of the overall and stage performance are presented. Details of the flow field from traverse measurements and the over tip shock structure obtained from high response pressure transducers are compared with predictions.

Strain Gauge results taken from the rotating blades are also presented.

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