Blade retention system for use in a gas turbine engine

Details Blade retention system for use in a gas turbine engine Blade retention system for use in a gas turbine engine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/30 (2006.01)

Patent

CA 2625591

The blade retention system comprises an annular sealing plate and a plurality of spaced--apart blade retention tabs having opposite first and second ends and a radially-orientated corrugated profile. The first ends of the tabs are connected to a first side face of the annular sealing plate. Each tab is configured and disposed to be inserted through a bottom portion of a respective one of the blade retention slots when the first side face of the sealing plate is positioned against one of the side faces of the rotor disc and covers an end side of the blade retention slots. The second end of each tab extends beyond the other of the side faces of the rotor disc and is bent to secure the annular sealing plate with reference to the rotor disc.

Affiliated with

Also associated with

Rating

Blade retention system for use in a gas turbine engine does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Blade retention system for use in a gas turbine engine, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Blade retention system for use in a gas turbine engine will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-1753047