# US 12,180,840 B1 · Seal assembly for a turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,180,840 B1 - Document ID: US12180840B1 - Status: Granted - Kind: B1 - Application number: 18/406,540 - Filed: 2024-01-08 - Granted: 2024-12-31 - Earliest claimed: 2024-01-08 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Rahul Anil Bidkar; Christopher Walter Falcone; Grant Robert Portune; Nora Marie Molino; Matthew James Misch - Web page: https://patentgrep.com/patent/US12180840B1 ## CPC - F01D 11/001: {for sealing space between stator blade and rotor} - F01D 11/005: {Sealing means between non relatively rotating elements} - F05D 2240/55: Seals - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A turbine engine includes a rotor, a stator having an aft wall, and a seal assembly having a plurality of seal segments disposed between the rotor and the stator. The rotor, the stator, and the seal assembly are arranged together to define a high pressure region and a low pressure region. The turbine engine also includes at least one biasing member engaged with one or more of the plurality of seal segments. The plurality of seal segments include a primary seal segment and a secondary seal segment connected together via a flexible joint. As such, the flexible joint allows for angular misalignment between the primary seal segment and the secondary seal segment, thereby allowing the primary seal segment to move with the rotor while the secondary seal segment maintains contact with the aft wall of the stator. ## Claims ### Claim 1 A turbine engine, comprising: a rotor; a stator comprising an aft wall; a seal assembly comprising a plurality of seal segments disposed between the rotor and the stator, wherein the rotor, the stator, and the seal assembly are arranged together to define a high pressure region and a low pressure region; and at least one biasing member engaged with one or more of the plurality of seal segments, wherein the plurality of seal segments comprise a primary seal segment and a secondary seal segment connected together via a flexible joint, and wherein the flexible joint comprises at least one of a pivot joint, a hinge joint, or a pin joint to allow for angular misalignment between the primary seal segment and the secondary seal segment, thereby allowing the primary seal segment to move with the rotor while the secondary seal segment maintains contact with the aft wall of the stator. ### Claim 2 (depends on 1) The turbine engine of claim 1, wherein the secondary seal segment is aft of the primary seal segment. ### Claim 3 (depends on 1) The turbine engine of claim 1, wherein the primary seal segment defines an L-shaped cross sectional shape in an axial direction of the turbine engine, the L-shaped cross sectional shape defining a flange. ### Claim 4 (depends on 3) The turbine engine of claim 3, wherein the secondary seal segment defines a generally rectangular cross-sectional shape in the axial direction of the turbine engine, the secondary seal segment positioned on the flange of the L-shaped cross sectional shape of the primary seal segment. ### Claim 5 (depends on 1) The turbine engine of claim 1, wherein at least one of the primary seal segment or the rotor further comprises at least one aerodynamic feature to allow for a formation of an air film between the plurality of seal segments and the rotor. ### Claim 6 (depends on 5) The turbine engine of claim 5, wherein the at least one aerodynamic feature comprises at least one of a Rayleigh pad, a spiral groove, or a herringbone groove. ### Claim 7 (depends on 1) The turbine engine of claim 1, further comprising an internal pocket on an aft side of at least one of the plurality of seal segments, the internal pocket surrounded on multiple sides by a secondary seal dam. ### Claim 8 (depends on 1) The turbine engine of claim 1, wherein the seal assembly further comprises a static seal arranged between the primary seal segment and the secondary seal segment. ### Claim 9 (depends on 8) The turbine engine of claim 8, wherein the static seal comprises at least one of a spline seal, a C-seal, an E-seal, a rope seal, or a W-seal. ### Claim 10 (depends on 1) The turbine engine of claim 1, wherein the at least one biasing member connects the plurality of seal segments to the stator and retracts the seal assembly away from the rotor in an absence of pressure. ### Claim 11 (depends on 1) The turbine engine of claim 1, wherein the at least one biasing member connects the plurality of seal segments to the stator and urges the seal assembly towards the rotor. ### Claim 12 (depends on 1) The turbine engine of claim 1, wherein the seal assembly further comprises one or more coatings to minimize radial friction or wear. ### Claim 13 A seal assembly for a turbine engine having a rotor and a stator, the seal assembly comprising: a plurality of seal segments, wherein, when arranged together, the rotor, the stator, and the seal assembly define a high pressure region and a low pressure region, the plurality of seal segments comprising a primary seal segment and a secondary seal segment connected together via a flexible joint; and at least one biasing member engaged with one or more of the plurality of seal segments, wherein the flexible joint comprises at least one of a pivot joint, a hinge joint, or a pin joint to allow wherein the flexible joint allows for angular misalignment between the primary seal segment and the secondary seal segment, thereby allowing the primary seal segment to move with the rotor while the secondary seal segment maintains contact with the aft wall of the stator. ### Claim 14 (depends on 13) The seal assembly of claim 13, wherein the secondary seal segment is aft of the primary seal segment, and wherein the primary seal segment defines a L-shaped cross sectional shape in an axial direction of the turbine engine, the L-shaped cross sectional shape defining a flange, and wherein the secondary seal segment defines a generally rectangular cross-sectional shape in the axial direction of the turbine engine, the secondary seal segment positioned on the flange of the L-shaped cross sectional shape of the primary seal segment. ### Claim 15 (depends on 13) The seal assembly of claim 13, wherein at least one of the primary seal segment or the rotor further comprises at least one aerodynamic feature to allow for a formation of an air film between the plurality of seal segments and the rotor. ### Claim 16 (depends on 15) The seal assembly of claim 15, wherein the at least one aerodynamic feature comprises at least one of a Rayleigh pad, a spiral groove, or a herringbone groove. ### Claim 17 (depends on 13) The seal assembly of claim 13, further comprising an internal pocket on an aft side of at least one of the plurality of seal segments, the internal pocket surrounded on multiple sides by a secondary seal dam. ### Claim 18 (depends on 13) The seal assembly of claim 13, wherein the seal assembly further comprises a static seal arranged between the primary seal segment and the secondary seal segment, and wherein the static seal comprises at least one of a spline seal, a C-seal, an E-seal, a rope seal, or a W-seal.