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US 9,316,119 B2Granted
Turbomachine secondary seal assembly
AssigneeUnited Technologies Corporation
InventorMasayoshi Sonokawa
Life of this patent
Estimating the term…
Abstract
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.
Claims21
A turbomachine ring seal assembly, comprising:
- a base that extends circumferentially about an axis, the base having an innermost diameter about the axis;
- and
- a 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.
3 more elements
A turbomachine seal assembly comprising:
- a first support that establishes a circumferential groove;
- a second support radially inboard the first support;
- and
- a 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.
3 more elements
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;
- and
- limiting 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.
1 more element
Dependencies are inferred from the claim text.