US 12,223,640 B2
Turbine blade creep monitoring
Adriano Pulisciano, Birmingham (GB); and Bilal M Nasser, Derby (GB)
Assigned to ROLLS-ROYCE PLC, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Apr. 4, 2022, as Appl. No. 17/712,676.
Claims priority of application No. 2106109 (GB), filed on Apr. 29, 2021.
Prior Publication US 2022/0351352 A1, Nov. 3, 2022
Int. Cl. G06T 7/00 (2017.01); F01D 5/14 (2006.01); F01D 25/00 (2006.01); G06T 7/593 (2017.01); G06T 7/80 (2017.01)
CPC G06T 7/001 (2013.01) [F01D 5/14 (2013.01); F01D 25/00 (2013.01); G06T 7/593 (2017.01); G06T 7/85 (2017.01); F05D 2220/323 (2013.01); F05D 2240/30 (2013.01); F05D 2260/80 (2013.01); F05D 2260/83 (2013.01); G06T 2207/10021 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A method of monitoring turbine blade creep in a gas turbine engine, the method including:
receiving stereo images of a turbine blade of a row of turbine blades, the stereo images being over a whole radial length of the turbine blade, and having been obtained using a stereo borescope located in the engine adjacent the row of turbine blades;
identifying a trailing edge, a platform edge, and a shroud edge of the blade in each of the stereo images;
mapping each of the trailing edge, the platform edge and the shroud edge by triangulation onto a 3D space;
measuring in the 3D space a distance between a radially inner landmark at a corner platform edge closest to the trailing edge, and a radially outer landmark at a corner of the shroud edge closest to the trailing edge on the blade; and
comparing the measured distance with the distance between the radially inner landmark and the radially outer landmark for a turbine blade that has not experienced creep to determine an amount of creep-induced distortion of the blade.