An example annular turbomachine seal includes an attachment portion, a first leg radially inward of the attachment portion, and a second leg radially inward of the attachment portion and configured to block flow from directly contacting an attachment associated with a bearing compartment of a turbom
An example annular turbomachine seal includes an attachment portion, a first leg radially inward of the attachment portion, and a second leg radially inward of the attachment portion and configured to block flow from directly contacting an attachment associated with a bearing compartment of a turbomachine.
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1. An annular turbomachine seal, comprising: an attachment portion;a first leg extending directly from the attachment portion radially inward of the attachment portion; anda second leg extending directly from the attachment portion radially inward of the attachment portion and configured to block fl
1. An annular turbomachine seal, comprising: an attachment portion;a first leg extending directly from the attachment portion radially inward of the attachment portion; anda second leg extending directly from the attachment portion radially inward of the attachment portion and configured to block flow from directly contacting a fastener associated with a bearing compartment of a turbomachine, wherein both the first leg and the second leg are configured to extend from the attachment portion on a first side of the fastener radially past the fastener to an opposing, second radial side of the fastener, the second leg axially spaced from the fastener; and wherein the turbomachine is a gas turbine engine. 2. The annular turbomachine seal of claim 1, wherein the second leg is configured to seal against the bearing compartment. 3. The annular turbomachine seal of claim 1, wherein second leg extends exclusively in a radial direction. 4. The annular turbomachine seal of claim 1, wherein the first leg extends axially forward of the second leg. 5. The annular turbomachine seal of claim 1, wherein at least a portion of the first leg and a portion of the second leg are radially aligned at a common radial position. 6. The annular turbomachine seal of claim 1, wherein at least a portion of the first leg and at least a portion of the second leg are radially aligned with the fastener at a common radial position. 7. The annular turbomachine seal of claim 1, wherein the attachment portion, the first leg, and the second leg are formed as a single monolithic structure. 8. The annular turbomachine seal of claim 1, including a third leg radially outward of the attachment portion, the third leg configured to provide a seal with a turbine section of the turbomachine. 9. The annular turbomachine seal of claim 1, wherein the attachment portion provides a plurality of apertures each configured to receive the fastener, the fastener securing the attachment portion directly to a low pressure turbine section of the turbomachine. 10. The annular turbomachine seal of claim 1, wherein the attachment portion, the first leg, and the second leg each extend circumferentially about an axis of the turbomachine. 11. The annular turbomachine seal of claim 1, wherein the fastener is a bearing compartment fastener. 12. A shield comprising: a wall spaced axially forward from at least a portion of a bearing compartment of a gas turbine engine, wherein the wall is configured to redirect an axial flow from a turbine section of the gas turbine engine, the axial flow moving toward the portion of the bearing compartment from a channel provided on a radially inner side by a turbine rotor and on a radially outer side by a leg extending directly from an attachment portion, the channel terminating at an outlet, the wall spaced axially downstream from the outlet relative to a direction of flow through the channel. 13. The shield of claim 12, wherein the wall extends from a first radial side of a bearing compartment fastener to an opposing, second radial side of the bearing compartment fastener. 14. The shield of claim 12, wherein a radially innermost end of the wall is configured to establish a seal with at least a portion of a bearing compartment. 15. The shield of claim 12, wherein the first wall is position axially between a high-pressure turbine and a low-pressure turbine of the gas turbine engine. 16. The shield of claim 12, wherein the wall extends radially outward past a heat shield of the bearing compartment. 17. The shield of claim 12, wherein the wall extends directly from the attachment portion. 18. A method of limiting thermal energy movement to a bearing compartment, comprising: moving flow through a channel toward a wall, the flow exiting the channel at an outlet, the channel provided by a shield and a turbine rotor, the wall downstream from the outlet relative to a general direction of through the channel; andredirecting flow from the channel away from a bearing compartment using the wall of the shield that is axially spaced from the channel; and wherein the bearing compartment is a bearing compartment of a gas turbine engine. 19. The method of claim 18, including sealing against the bearing compartment with the wall.
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