Compressor blades are among the numerous and complicated parts of gas turbine engines. A freeform surface of compressor blades is characterized by a complex of parameters distinguishing the geometry of their individual sections. The paper presents a model of calculating a complex of geometric parameters of blade profiles by a measured array of points. A method of estimating the uncertainty of measurement of a set of geometrical parameters with the use of coordinate measuring machines is developed. Software algorithms have been designed for the implementation of the proposed models and methods. The paper presents the results of analyzing errors of measurement of a set of geometrical parameters of the gas turbine engine compressor blade airfoil. We obtained the probabilistic characteristics of arising errors for three cross sections of the blade airfoil. The proposed models and algorithms for computing a complex of geometric parameters of the measured profiles by an array of points can be applied to software for measuring machines.


    Access

    Download


    Export, share and cite



    Title :

    Study of uncertainty of measuring geometrical parameters of gas turbine engine compressor blade profiles


    Contributors:


    Publication date :

    2016




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown





    Noninterference Technique for Measurement of Turbine Engine Compressor Blade Stress

    P. E. McCarty / J. W. Thompson R. S. Ballard | AIAA | 1982


    Jet engine compressor blade

    Emerald Group Publishing | 1999


    Turbine/compressor blade measurement system

    Emerald Group Publishing | 2001


    Gas Turbine Aero Engine Compressor Blade Erosion and Heat Resistant Coatings

    Savkov, K. / Doroshko, S. / Urbaha, M. et al. | British Library Conference Proceedings | 2011