# US 10,480,351 B2 · Segmented liner > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,480,351 B2 - Document ID: US10480351B2 - Status: Granted - Kind: B2 - Application number: 15/583,015 - Filed: 2017-05-01 - Published: 2018-11-01 - Granted: 2019-11-19 - Earliest claimed: 2017-05-01 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Mohand-Ouamar Nait Atmane; Filip Skurla; Krunoslav Igercic; Petar Jakovic; Igor Cvjetko - Web page: https://patentgrep.com/patent/US10480351B2 ## CPC - F01D 25/30: Exhaust heads, chambers, or the like - F01D 25/145: {Thermally insulated casings} - F23R 3/00: Continuous combustion chambers using liquid or gaseous fuel - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F23R 3/60: Support structures; Attaching or mounting means - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A turbomachine, e.g., a gas turbine, includes a compressor, a combustion section downstream from the compressor, a turbine downstream from the combustion section and an exhaust section downstream from the turbine. The exhaust section includes a diffuser. The diffuser includes an outer casing and a liner radially inward of the outer casing. The liner includes a plurality of discrete liner panels. The diffuser further includes a plurality of radial support members extending radially inward from the outer casing. The diffuser also includes a plurality of axial support members disposed proximate to the liner. ## Claims ### Claim 1 A component of a turbomachine, the component comprising: an outer casing; a liner radially inward of the outer casing, the liner comprising a plurality of discrete liner panels; a plurality of radial support members extending radially inward from the outer casing; and a plurality of axial support members disposed inward of the liner along a radial direction. ### Claim 2 (depends on 1) The component of claim 1, wherein the plurality of axial support members are disposed between the liner and the plurality of radial support members along the radial direction. ### Claim 3 (depends on 1) The component of claim 1, further comprising a bracket mounted to each radial support member of the plurality of radial support members at an end of the radial support member distal from the outer casing, each bracket extending orthogonally to the respective radial support member. ### Claim 4 (depends on 3) The component of claim 3, wherein each bracket comprises a threaded fastener. ### Claim 5 (depends on 4) The component of claim 4, wherein the threaded fasteners of the brackets comprise a first plurality of threaded fasteners, the component further comprising a second plurality of threaded fasteners positioned radially inward of the plurality of axial support members, one of the first plurality of threaded fasteners and the second plurality of threaded fasteners comprising a plurality of externally threaded fasteners, the other of the first plurality of threaded fasteners and the second plurality of threaded fasteners comprising a plurality of internally threaded fasteners, each externally threaded fastener configured to threadedly engage with a respective one of the plurality of internally threaded fasteners. ### Claim 6 (depends on 5) The component of claim 5, wherein the plurality of axial support members comprises a plurality of forward axial support members, a plurality of intermediate axial support members, and a plurality of aft axial support members, each of the plurality of axial support members of the plurality of forward axial support members comprises a hole for receiving a respective one of the plurality of externally threaded fasteners, and each axial support member of the plurality of aft axial support members comprises a hole for receiving a respective one of the plurality of externally threaded fasteners. ### Claim 7 (depends on 1) The component of claim 1, further comprising a plurality of circumferential support members extending between adjacent axial support members of the plurality of axial support members. ### Claim 8 A component of a turbomachine, the component comprising: an outer casing; a liner radially inward of the outer casing, the liner comprising a plurality of discrete liner panels; a plurality of radial support members extending radially inward from the outer casing; and a plurality of axial support members disposed proximate to the liner, wherein the plurality of axial support members comprises a plurality of outer axial support members disposed outward of the liner between the liner and the plurality of radial support members along a radial direction and a plurality of inner axial support members disposed inward of the liner along the radial direction. ### Claim 9 (depends on 1) The component of claim 1, wherein at least one panel of the plurality of discrete liner panels comprises a plurality of discrete segments. ### Claim 10 (depends on 9) The component of claim 9, further comprising a plurality of externally threaded fasteners extending between the plurality of inner axial support members and the outer axial support members along the radial direction, each externally threaded fastener of the plurality of externally threaded fasteners extending proximate to an edge of one of the plurality of discrete segments. ### Claim 11 (depends on 10) The component of claim 10, wherein each axial support member of one of the plurality of inner axial support members and the plurality of outer axial support members comprises a plurality of holes, each hole of the plurality of holes receiving a corresponding one of the plurality of externally threaded fasteners. ### Claim 12 (depends on 11) The component of claim 11, further comprising a plurality of plates positioned between the plurality of internally threaded fasteners and the plurality of discrete segments along the radial direction, each plate comprising a hole, and a respective externally threaded fastener of the plurality of externally threaded fasteners extending through the hole of each plate. ### Claim 13 (depends on 10) The component of claim 10, further comprising a plurality of internally threaded fasteners, each internally threaded fastener of the plurality of internally threaded fasteners configured to threadedly engage with a corresponding one of the externally threaded fasteners. ### Claim 14 A gas turbine, comprising: a compressor, a combustion section downstream from the compressor, a turbine downstream from the combustion section, an exhaust section downstream from the turbine, and a component, the component comprising: an outer casing; a liner radially inward of the outer casing, the liner comprising a plurality of discrete liner panels; a plurality of radial support members extending radially inward from the outer casing; a plurality of axial support members disposed proximate to the liner; and a bracket mounted to each radial support member of the plurality of radial support members at an end of the radial support member distal from the outer casing, each bracket extending orthogonally to the respective radial support member. ### Claim 15 (depends on 14) The gas turbine of claim 14, wherein the liner comprises a plurality of panels, one or more of the plurality of panels comprising a plurality of segments. ### Claim 16 (depends on 14) The gas turbine of claim 14, wherein the plurality of axial support members comprises a plurality of outer axial support members disposed outward of the liner between the liner and the plurality of radial support members along the radial direction and a plurality of inner axial support members disposed inward of the liner along the radial direction. ### Claim 17 (depends on 14) The gas turbine of claim 14, further comprising a plurality of circumferential support members extending between adjacent axial support members of the plurality of axial support members.