Bearing compartment seal configuration for a gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsJonathan Logan Miller, M. Rifat Ullah
Life of this patent
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Abstract
A bearing compartment seal for a gas turbine engine includes at least one seal ring defining an axis and having a radially inward facing sealing surface and a seal runner having a support constructed of a first material and an interface portion constructed of a second material. The interface portion includes a radially outward facing surface. A first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.
Claims18
A bearing compartment seal for a gas turbine engine comprising:
- at least one seal ring defining an axis and having a radially inward facing sealing surface;
- a seal runner having a support portion constructed of a first material and an interface portion constructed of a second material distinct from the first material, the interface portion including a radially outward facing surface, the support portion including a radial section having a radially inward facing surface and an axial section extending axially from an end of the radial section, the axial section including a radially outward facing surface contacting the interface portion, the interface portion including a uniform radial thickness along a contact with the seal ring;
- and
- wherein a first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.
A bearing compartment seal for a gas turbine engine comprising:
- at least one seal ring defining an axis and having a radially inward facing sealing surface;
- a seal runner having a support portion constructed of a first material and an interface portion constructed of a second material distinct from the first material, the interface portion including a radially outward facing surface, the support portion including a radial section having a radially inward facing surface and an axial section extending axially from an end of the radial section, the axial section including a radially outward facing surface contacting the interface portion;
- and
- wherein a first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring;
- and
- wherein the interface portion is disposed circumferentially about the support portion, and extends at least a full axial length of the at least one seal ring, wherein the support portion includes a radially outward extending axial retention tab at at least one axial end of the support portion, the axial retention tab being circumferentially intermittent and being configured to retain the interface portion axially relative to the support portion.
A bearing compartment seal for a gas turbine engine comprising:
- at least one seal ring defining an axis and having a radially inward facing sealing surface;
- a seal runner having a support portion constructed of a first material and an interface portion constructed of a second material distinct from the first material, the interface portion including a radially outward facing surface, the support portion including a radial section having a radially inward facing surface and an axial section extending axially from an end of the radial section, the axial section including a radially outward facing surface contacting the interface portion, the interface portion is retained relative to the support portion at least partially via a fastener, wherein the fastener protrudes through the interface portion and the support portion;
- and
- wherein a first coefficient of thermal expansion of the second material is at most approximately equal to a second coefficient of thermal expansion of the at least one seal ring.
Dependencies are inferred from the claim text.