Abstract
The proposed mathematical model permits assessment of the uncertainties in measuring the profile of compressor blades in a gas-turbine engine. The following geometric parameters may be calculated by means of the model: the radius of the input and output edges; the maximum profile thickness; the profile thickness at the input and output edges; and the chord width. The model may be used to determine the probability characteristics of the uncertainties in measuring the compressor-blade profile in a gas-turbine engine.
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