An exemplary turbomachine secondary ring seal assembly includes a base portion that extends circumferentially about an axis and a protrusion extending from the base portion toward the axis. The protrusion has a sealing surface that contacts a support to limit movement of a fluid from a first axial s
An exemplary turbomachine secondary ring seal assembly includes a base portion that extends circumferentially about an axis and a protrusion extending from the base portion toward the axis. The protrusion has a sealing surface that contacts a support to limit movement of a fluid from a first axial side of the base portion to a second opposite axial side of the base portion. The sealing surface faces the axis. The sealing surface may also face in a radial direction.
대표청구항▼
1. A turbomachine ring seal assembly, comprising: a base that extends circumferentially about an axis, the base having an innermost diameter about the axis; anda protruding element extending radially inward and axially forward from the base, the protruding element having a first sealing surface that
1. A turbomachine ring seal assembly, comprising: a base that extends circumferentially about an axis, the base having an innermost diameter about the axis; anda protruding element extending radially inward and axially forward from the base, the protruding element having a first sealing surface that contacts a first support to limit movement of a fluid from a first axial side of the base to a second opposite axial side of the base, the contact between the first sealing surface and the first support at a position that is radially inside the innermost diameter of the base,the protruding element having a second sealing surface that contacts a second support to limit movement of the fluid from the first axial side of the base to the second opposite axial side of the base, the contact between the second sealing surface and the second support at a position that is radially inside the innermost diameter of the base,wherein the first sealing surface faces the axis, and the first sealing surface is transverse to the second sealing surface. 2. The turbomachine ring seal assembly of claim 1, including a flange extending axially from the base away from the second sealing surface. 3. The turbomachine ring seal assembly of claim 1, wherein the innermost diameter of the base has a first axial width, and the first sealing surface has a second axial width smaller than the first axial width. 4. A turbomachine seal assembly comprising: a first support that establishes a circumferential groove;a second support radially inboard the first support; anda seal having a base and a protruding element extending radially inward and axially forward from the base, the base at least partially received within the circumferential groove, wherein the protruding element contacts the second support to restrict flow of a fluid from a first axial side of the circumferential groove to a second opposite axial side of the circumferential groove,wherein the base has a single innermost diameter and the protruding element contacts a radially extending surface of the first support when the seal is in the sealing position, a contact interface between the protruding element and the first support extending from a position radially outside the single innermost diameter to a position that is radially inside the single innermost diameter. 5. The turbomachine seal assembly of claim 4, wherein the seal is configured to restrict flow of the fluid from an area outside a bearing compartment to an area inside the bearing compartment. 6. The turbomachine seal assembly of claim 4, wherein the protruding element contacts an axially extending surface of the second support when the seal is in a sealing position. 7. The turbomachine seal assembly of claim 4, wherein the base is radially spaced from the first support when the seal is in the sealing position. 8. The turbomachine seal assembly of claim 4, wherein the seal is positioned within a gas turbine engine. 9. The turbomachine seal assembly of claim 4, where in the seal is a contracting seal. 10. A turbomachine sealing method including: positioning a seal at least partially within a circumferential groove of a first support;supporting the seal radially inward against a second support assembly using a pressurized fluid, a self-contracting force of ring seal, or both; andlimiting flow of a fluid using the seal by contacting the first support and the second support with surfaces of a common protruding element of the seal, the protruding element extending radially inward and axially forward from a base of the seal, the contact between the first support and the second support at positions that are radially inside a radially innermost diameter of the base. 11. The turbomachine sealing method of claim 10, wherein the limiting includes limiting flow of a fluid into a bearing compartment of the turbomachine. 12. The turbomachine ring seal assembly of claim 1, wherein the second seal surface interfaces directly with the sealing surface that faces the axis at a circumferentially extending corner of the protruding element. 13. The turbomachine seal assembly of claim 4, wherein the protruding element contacts an axially extending surface of the second support when the seal is in the sealing position, and both the radially extending surface contacted by the protrusion and the axially extending surface contacted by the protruding element have portions that are closer to the second axial side of the circumferential groove than the base. 14. The turbomachine sealing method of claim 10, the contacting of the first support is at a position that is upstream from the base of the seal relative to a direction of flow through the turbomachine. 15. The turbomachine sealing method of claim 10, including biasing the protruding element axially forward within the turbomachine using the pressurized fluid. 16. The turbomachine ring seal assembly of claim 1, wherein the first and second sealing surfaces of the protruding element extend circumferentially continuously about the axis from a first side of a split to an opposing second side of the split, the split extending radially through both the base and protruding element. 17. The turbomachine seal assembly of claim 4, wherein the protruding element extends circumferentially continuously about the axis from a first side of a split to an opposing second side of the split, the split extending radially through both the base and protruding element. 18. The turbomachine sealing method of claim 13, wherein contact between the protruding element and the axially extending surface, and contact between the protruding element and the radially extending surface is circumferentially continuous about the axis from a first side of a split to an opposing second side of the split, the split extending radially through both the base and protruding element. 19. The turbomachine seal assembly of claim 4, wherein the first support and the second support are components of a turbomachine. 20. The turbomachine seal assembly of claim 4, further comprising a flange extending axially from the base away from the second sealing surface. 21. The turbomachine sealing method of claim 10, wherein the seal further comprises a flange extending from a base portion of the seal in an axial direction away from the common protruding element of the seal.
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