US 12,716,367 B1Granted

Bearing support having arcuate damper elements

AssigneePratt & Whitney Canada Corp.

InventorsNathan Tomes, Tyler Richardson

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Abstract

Bearing damper systems for gas turbine engines include a bearing structure and, a housing arranged outward from the bearing structure and defining a plurality of axially extending recesses arranged circumferentially about the axis. A set of energy dissipating elements are arranged within the recesses and are axially constrained therein. The energy dissipating elements are arranged to receive a radial outward force from the bearing structure. Each energy dissipating element may be radially compressed while being axially constrained in response to a radial movement of the bearing structure and enter a loaded state with energy associated with the compression is absorbed into the material of the energy dissipating element. Each energy dissipating element is configured to convert at least a portion of the absorbed energy to heat and is configured to return to an unloaded state after removal of the load from the bearing structure.

Claims20

Dependent claims

A bearing damper system for a gas turbine engine comprising:

a bearing structure arranged about an axis;
a housing arranged radially outward from the bearing structure relative to the axis, the housing defining a plurality of axially extending recesses arranged circumferentially about the axis;
and
a set of energy dissipating elements, wherein one energy dissipating element of the set of energy dissipating elements is arranged within each recess of the housing and axially constrained within the respective recess, the energy dissipating elements arranged to receive a radial outward force from the bearing structure,
wherein each energy dissipating element is arranged to be radially compressed while being axially constrained in response to a radial movement of the bearing structure toward the respective energy dissipating element and enter a loaded state wherein energy associated with said compression is absorbed into a material of the respective energy dissipating element,
wherein each energy dissipating element is configured to convert at least a portion of the absorbed energy to heat, and
wherein each energy dissipating element is configured to return to an unloaded state after removal of a load from the bearing structure.

4 more elements

An aircraft engine comprising:

a rotating component defining an axis;
a bearing structure configured to rotationally support the rotating component;
and
a bearing damper system comprising:
a housing arranged radially outward from the bearing structure relative to the axis, the housing defining a plurality of axially extending recesses arranged circumferentially about the axis;
and
a set of energy dissipating elements, wherein one energy dissipating element of the set of energy dissipating elements is arranged within each recess of the housing and axially constrained within the respective recess, the energy dissipating elements arranged to
receive a radial outward force from the bearing structure,
wherein each energy dissipating element is arranged to be radially compressed while being axially constrained in response to a radial movement of the bearing structure toward the respective energy dissipating element and enter a loaded state wherein energy associated with said compression is absorbed into a material of the respective energy dissipating element,
wherein each energy dissipating element is configured to convert at least a portion of the absorbed energy to heat, and
wherein each energy dissipating element is configured to return to an unloaded state after removal of a load from the bearing structure.

8 more elements

Dependencies are inferred from the claim text.