Slip based radial bearing support
A bearing arrangement of a gas turbine engine includes a first bearing and a second bearing axially offset from the first bearing. A first bearing support extends from a bearing housing to the first bearing to support the first bearing, and a second bearing support extends from the bearing housing to the second bearing to support the second bearing. One or more radial bearing supports including a plurality of radial spokes extend between the bearing housing and the second bearing. Each spoke extends from a spoke base to a spoke tip. A raised pedestal is positioned at a contact point of each spoke tip, and at least one destabilizer is secured to the second bearing and is configured to contact at least one radial spoke when the predetermined threshold is exceeded to initiate sliding of the plurality of radial spokes from their respective raised pedestal.
1 . A bearing arrangement of a gas turbine engine, comprising:
a first bearing supportive of a shaft;
a second bearing axially offset from the first bearing and supportive of the shaft;
a first bearing support extending from a bearing housing to the first bearing to support the first bearing;
a second bearing support extending from the bearing housing to the second bearing to support the second bearing;
one or more radial bearing supports including a plurality of radial spokes extending between the bearing housing and the second bearing, each spoke extending from a spoke base to a spoke tip;
a raised pedestal disposed at a contact point of each spoke tip; and
at least one destabilizer secured to the second bearing and configured to contact at least one radial spoke of the plurality of radial spokes when a displacement of the second bearing exceeds a predetermined threshold to initiate sliding of the plurality of radial spokes with respect to a corresponding raised pedestal.
2 . The bearing arrangement of claim 1 , wherein the one or more radial bearing supports includes an outer ring disposed at the bearing housing, and the plurality of radial spokes extending from the spoke base secured to the outer ring to the spoke tip at the second bearing.
3 . The bearing arrangement of claim 2 , wherein each raised pedestal extends radially outwardly from a bearing outer race of the second bearing.
4 . The bearing arrangement of claim 3 , further comprising a secondary pedestal extending radially outwardly from the bearing outer race defining a channel between each raised pedestal and the secondary pedestal.
5 . The bearing arrangement of claim 1 , wherein the destabilizer is configured to contact the plurality of radial spokes in an axial direction in response to a tilt displacement of the second bearing.
6 . The bearing arrangement of claim 5 , wherein the destabilizer is configured to contact the plurality of radial spokes at a point closer to the second bearing than to the spoke base.
7 . The bearing arrangement of claim 1 , wherein the one or more radial bearing supports includes an inner ring surrounding the second bearing, and the plurality of radial spokes extend radially outwardly from the spoke base connected to the inner ring to the spoke tip.
8 . The bearing arrangement of claim 7 , wherein the contact point is defined between the spoke tip and a bumper extending radially inwardly from the bearing housing.
9 . The bearing arrangement of claim 8 , wherein the destabilizer is configured to contact the plurality of radial spokes at a point closer to the bumper than to the second bearing.
10 . The bearing arrangement of claim 1 , further comprising a roller element disposed at the contact point.
11 . 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 first bearing;
a second bearing axially offset from the first bearing;
a first bearing support extending from a bearing housing to the first bearing to support the first bearing;
a second bearing support extending from the bearing housing to the second bearing to support the second bearing;
one or more radial bearing supports including a plurality of radial spokes extending between the bearing housing and the second bearing, each spoke extending from a spoke base to a spoke tip;
a raised pedestal disposed at a contact point of each spoke tip; and
at least one destabilizer secured to the second bearing and configured to contact at least one radial spoke of the plurality of radial spokes when a displacement of the second bearing exceeds a predetermined threshold to initiate sliding of the plurality of radial spokes with respect to a corresponding raised pedestal.
12 . The gas turbine engine of claim 11 , wherein the one or more radial bearing supports includes an outer ring disposed at the bearing housing, and the plurality of radial spokes extend from the spoke base secured to the outer ring to the spoke tip at the second bearing.
13 . The gas turbine engine of claim 12 , wherein each raised pedestal extends radially outwardly from a bearing outer race of the second bearing.
14 . The gas turbine engine of claim 13 , further comprising a secondary pedestal extending radially outwardly from the bearing outer race defining a channel between each raised pedestal and the secondary pedestal.
15 . The gas turbine engine of claim 11 , wherein the destabilizer is configured to contact the plurality of radial spokes in an axial direction in response to a tilt displacement of the second bearing.
16 . The gas turbine engine of claim 15 , wherein the destabilizer is configured to contact the plurality of radial spokes at a point closer to the second bearing than to the spoke base.
17 . The gas turbine engine of claim 11 , wherein the one or more radial bearing supports includes an inner ring surrounding the second bearing, and the plurality of radial spokes extend radially outwardly from the spoke base secured to the inner ring to the spoke tip.
18 . The gas turbine engine of claim 17 , wherein the contact point is defined between the spoke tip and a bumper extending radially inwardly from the bearing housing.
19 . The gas turbine engine of claim 18 , wherein the destabilizer is configured to contact the plurality of radial spokes at a point closer to the bumper than to the second bearing.
20 . The gas turbine engine of claim 11 , further comprising a roller element disposed at the contact point.