METHOD OF DETERMINING STATOR SHELL DEFORMATION OF AIRCRAFT GAS TURBINE ENGINE PROPELLER Russian patent published in 2009 - IPC G01B7/14 

FIELD: physics; measurement.

SUBSTANCE: present invention pertains to measuring technology and can be used for determining deformation of the stator shell of the propulsion unit propeller of an aircraft gas turbine engine in places of fitting cluster single-turn eddy current sensors and displacement of the geometrical centre of the shell relative the centre of rotation of the propeller. Evaluation of deformation of the stator shell and displacement of the geometrical centre relative the centre of rotation of the propeller is done by combined processing of results: 1) measurement of radial gaps between edges of propeller blades and detecting elements of the cluster single-turn eddy current sensor, which are not less than four and are uniformly arranged along the perimeter of the geometrical centre on the level of its inner surface inside the zone of interaction of the electromagnetic field of the detecting elements of the sensor with the edge of the propeller blade, obtained in the "dry motoring" move before testing; 2) similar measurements of radial gaps, but in working modes; 3) numerical modelling of elastic and temperature deformation of blades on regularly measured values of the propeller rotation frequency and temperature of the medium in which the propeller is located.

EFFECT: detection and quantitative evaluation of deformation of the stator shell and displacement of the geometrical centre of rotation of the propeller.

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