The influence of a number of points on results of measurements of a turbine blade
Aircraft Engineering and Aerospace Technology
ISSN: 0002-2667
Article publication date: 2 October 2017
Abstract
Purpose
The purpose of this paper was to determine the influence of a number of measured points on results of measurements of turbine blades, which are the parts of aircraft engines. The selection of a number of points is the part of a measurement strategy in the coordinate measuring technique and determines the accuracy of measurements.
Design/methodology/approach
Numerical and experimental investigations were conducted. The measurements were simulated using different numbers of measured points. The simulated measurements were performed for the selected dispersion of measured points. The dispersion reflected the inaccuracy of a manufacturing process of the considered product and the uncertainty of measurements of curvilinear surfaces. To verify the accuracy of the numerical studies, experimental research was conducted. The real measurements were conducted using the selected coordinate measuring machine.
Findings
The gained results following the simulations can be very useful when selecting the appropriate number of measured points. The chosen number of points may be used during real measurements of turbine blades conducted on coordinate measuring machines. The results of numerical research indicate that there should be used the average radii of leading and trailing edges to increase the accuracy of measurements. The results of real coordinate measurements confirmed the results of simulation studies.
Originality/value
The main novelty of the paper is the presented methodology for determining the influence of measured points on results of measurements. The presented methodology helps the user of a coordinate measuring system select the appropriate measurement strategy of free-form surfaces applied in the aerospace industry.
Keywords
Citation
Magdziak, M. (2017), "The influence of a number of points on results of measurements of a turbine blade", Aircraft Engineering and Aerospace Technology, Vol. 89 No. 6, pp. 953-959. https://doi.org/10.1108/AEAT-03-2016-0044
Publisher
:Emerald Publishing Limited
Copyright © 2017, Emerald Publishing Limited