CPC F01D 21/045 (2013.01) [F01D 5/026 (2013.01); F01D 5/066 (2013.01); F02C 3/107 (2013.01); F02C 7/36 (2013.01); F16D 1/10 (2013.01); F05D 2240/61 (2013.01); F05D 2250/182 (2013.01); F05D 2260/4031 (2013.01); F05D 2260/902 (2013.01); F16D 2001/103 (2013.01); Y10T 403/16 (2015.01); Y10T 403/559 (2015.01); Y10T 403/7045 (2015.01)] | 7 Claims |
1. A toothed coupling mechanism for an assembly of rotating elements of an aircraft gas turbine engine, comprising:
a first coupling half and a second coupling half having an axial toothed coupling interface therebetween, the first coupling half having a plurality of first splined teeth, each first splined tooth has a first axial free end, the second coupling half having a plurality of second splined tooth, each second splined tooth having a second axial free end, the first splined teeth being inter-engaged about an axis with the second splined teeth in a situation of splined teeth engagement, for transmitting torque between the first coupling half and the second coupling half; and
a protrusion located, away from said axis, on the free end of one of the second splined teeth,
said protrusion projects from the free end of said one of the second splined tooth at a surrounding shoulder and
one of the first splined tooth is configured to come into contact with said protrusion in a situation of splined teeth disengagement.
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