Closed channel disk for a gas turbine engine

Details Closed channel disk for a gas turbine engine Closed channel disk for a gas turbine engine

F - Mech Eng,Light,Heat,Weapons

01

D

26/148, 170/72

F01D 5/02 (2006.01) B23P 15/00 (2006.01) F01D 5/30 (2006.01) F02C 7/00 (2006.01)

Patent

CA 1050893

ABSTRACT OF THE DISCLOSURE A disk having a closed channel construction and which is especially suited for supporting the rotating blades of a gas turbine engine is disclosed. In one embodiments, the disk support the fan blades of a turbofan engine which extend radially hterefrom. The disk structurally includes an upstream web, a downstream web and a plurality of arcuate plugs disposed in end to end relationship between the webs to form a toroidal type structure having a substantially rectangu- lar cross section. The disk is contoured to provide a level of torsional and bending stiffness which limits the most critical stage vibratory frequencies to values above the engine operating range while limiting the maximum value of the disk hoop stress during operation to 8 level below the durability limits of the disk material utilized. A method for making the disk is further disclosed. -1-

246778

Affiliated with

Also associated with

Rating

Closed channel disk for 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 Closed channel disk for a gas turbine engine, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Closed channel disk for a gas turbine engine will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-1077073