Buckling spoked frangible bearing support
A bearing arrangement of a gas turbine engine includes a bearing supportive of a shaft, a bearing support extending from the bearing housing to the bearing to support the bearing, and one or more radial bearing supports including a plurality of radial spokes extending between the bearing housing and the bearing. The plurality of radial spokes are configured to buckle under compression when radial loads at the bearing exceed a predetermined threshold.
1 . A bearing arrangement of a gas turbine engine, comprising:
a bearing disposed in a bearing housing and supportive of a shaft;
a bearing support extending from the bearing housing to the bearing to support the bearing; and
one or more radial bearing supports including a plurality of radial spokes extending between the bearing housing and the bearing, the plurality of radial spokes configured to buckle under compression when radial loads at the bearing exceed a predetermined threshold;
wherein a spoke tip of each of the radial spokes are configured to contact the bearing while not being secured thereto.
2 . The bearing arrangement of claim 1 , wherein the radial bearing support includes an outer ring disposed at the bearing housing, and the plurality of radial spokes extend from the outer ring to the bearing.
3 . The bearing arrangement of claim 1 , further comprising one or more bumpers axially offset from the radial bearing support configured to limit radial travel of the bearing.
4 . The bearing arrangement of claim 3 , wherein the plurality of spokes are configured to buckle tangentially.
5 . The bearing arrangement of claim 4 , wherein the one or more bumpers is two bumpers, and the radial bearing support is disposed axially between the two bumpers.
6 . The bearing arrangement of claim 1 , wherein the radial bearing support includes an inner ring disposed at the bearing, and the plurality of radial spokes extend from the inner ring to the bearing housing.
7 . The bearing arrangement of claim 6 , wherein the plurality of radial spokes are not secured to the bearing housing.
8 . The bearing arrangement of claim 1 , wherein the one or more radial supports includes a first radial support and a second radial support axially offset from the first radial support.
9 . The bearing arrangement of claim 8 , further comprising a bumper disposed axially between the first radial support and the second radial support.
10 . A gas turbine engine, comprising:
a combustor;
a turbine driven by combustion products of the combustor;
a shaft driven by rotation of the turbine; and
a bearing arrangement supportive of the shaft, the bearing arrangement including:
a bearing disposed in a bearing housing;
a bearing support extending from the bearing housing to the bearing to support the bearing; and
one or more radial bearing supports including a plurality of radial spokes extending between the bearing housing and the bearing, the plurality of radial spokes configured to buckle under compression when radial loads at the bearing exceed a predetermined threshold;
wherein a spoke tip of each of the radial spokes are configured to contact the bearing while not being secured thereto.
11 . The gas turbine engine of claim 10 , wherein the radial bearing support includes an outer ring disposed at the bearing housing, and the plurality of radial spokes extend from the outer ring to the bearing.
12 . The gas turbine engine of claim 10 , further comprising one or more bumpers axially offset from the radial bearing support configured to limit radial travel of the bearing.
13 . The gas turbine engine of claim 12 , wherein the plurality of spokes are configured to buckle tangentially.
14 . The gas turbine engine of claim 13 , wherein the one or more bumpers is two bumpers, and the radial bearing support is disposed axially between the two bumpers.
15 . The gas turbine engine of claim 10 , wherein the radial bearing support includes an inner ring disposed at the bearing, and the plurality of radial spokes extend from the inner ring to the bearing housing.
16 . The gas turbine engine of claim 15 , wherein the plurality of radial spokes are not secured to the bearing housing.
17 . The gas turbine engine of claim 10 , wherein the one or more radial supports includes a first radial support and a second radial support axially offset from the first radial support.
18 . The gas turbine engine of claim 10 , further comprising a bumper disposed axially between the first radial support and the second radial support.