# US 11,441,440 B2 · Rotor assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,441,440 B2 - Document ID: US11441440B2 - Status: Granted - Kind: B2 - Application number: 16/859,569 - Filed: 2020-04-27 - Published: 2021-10-28 - Granted: 2022-09-13 - Earliest claimed: 2020-04-27 - Assignees: Raytheon Technologies Corporation - Applicants: Raytheon Technologies Corporation - Inventors: William S. Pratt; Christopher J. Knortz - Web page: https://patentgrep.com/patent/US11441440B2 ## CPC - F01D 11/001: {for sealing space between stator blade and rotor} - F01D 5/3007: {of axial insertion type} - F01D 5/3015: {with side plates} - F01D 11/00: Preventing or minimising internal leakage of working-fluid, e.g. between stages (sealings in general F16J {; sealing arrangements for transition ducts of combustor cans F01D9/023}) - F01D 11/005: {Sealing means between non relatively rotating elements} - F01D 5/082: {on the side of the rotor disc} - F01D 11/006: {Sealing the gap between rotor blades or blades and rotor} - F05D 2220/3216: for a special compressor stage - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2230/60: Assembly methods - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor - F05D 2240/55: Seals - F05D 2240/80: Platforms for stationary or moving blades - F05D 2260/30: Retaining components in desired mutual position - 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 rotor assembly for a piece of rotational equipment includes a rotor disk configured to rotate about a rotational axis. The rotor disclose includes a first rotor attachment member including a first mount slot and a second rotor attachment member including a second mount slot. The rotor disk further includes an outer diameter surface extending between the first rotor attachment member and the second rotor attachment member. The rotor assembly further includes a rotor blade including an airfoil, a platform, a first mount portion retained within the first mount slot, and a second mount portion retained within the second mount slot. The platform includes an inner platform surface facing the outer diameter surface. The rotor disk and the rotor blade define a circumferential portion of a circumferentially-extending cavity between the inner platform surface, the outer diameter surface, the first rotor attachment member, and the second rotor attachment member. ## Claims ### Claim 1 A rotor assembly for a piece of rotational equipment, the rotor assembly comprising: a rotor disk configured to rotate about a rotational axis, the rotor disk comprising a first rotor attachment member comprising a first mount slot and a second rotor attachment member comprising a second mount slot, the rotor disk further comprising an outer diameter surface extending between the first rotor attachment member and the second rotor attachment member; a rotor blade comprising an airfoil, a platform, a first mount retained within the first mount slot, and a second mount retained within the second mount slot, the platform comprising an inner platform surface facing the outer diameter surface of the rotor disk, wherein the rotor disk and the rotor blade define a circumferential portion of a circumferentially-extending cavity between the inner platform surface, the outer diameter surface of the rotor disk, the first rotor attachment member, and the second rotor attachment member; and a seal disposed within the circumferentially-extending cavity, the seal comprising at least one sealing ring disposed about the rotational axis, the at least one sealing ring in contact with the inner platform surface of the platform and radially spaced from the outer diameter surface of the rotor disk. ### Claim 2 (depends on 1) The rotor assembly of claim 1, wherein each of the first rotor attachment member and the second rotor attachment member extend radially outward from the outer diameter surface of the rotor disk to respective first and second distal ends adjacent the inner platform surface of the platform. ### Claim 3 (depends on 2) The rotor assembly of claim 2, wherein the first mount slot and the second mount slot extend a first radial distance from the respective first and second distal ends toward the outer diameter surface of the rotor disk and wherein the first mount slot and the second mount slot are spaced from the outer diameter surface of the rotor disk by a second radial distance. ### Claim 4 (depends on 1) The rotor assembly of claim 1, wherein the circumferentially-extending cavity comprises an axial width extending from the first rotor attachment member to the second rotor attachment member and a radial height extending from the outer diameter surface of the rotor disk to the inner platform surface of the platform. ### Claim 5 (depends on 1) The rotor assembly of claim 1, wherein the at least one sealing ring is biased in a radially outward direction. ### Claim 6 (depends on 1) The rotor assembly of claim 1, wherein the at least one sealing ring is in contact with a cavity-facing surface of one or both of the first rotor attachment member and the second rotor attachment member. ### Claim 7 (depends on 1) The rotor assembly of claim 1, wherein the at least one sealing ring comprises a first sealing ring and a second sealing ring axially adjacent the first sealing ring. ### Claim 8 (depends on 7) The rotor assembly of claim 7, wherein the first sealing ring is axially spaced from the second sealing ring. ### Claim 9 (depends on 8) The rotor assembly of claim 8, wherein the inner platform surface of the platform comprises two axially-adjacent recesses, the first sealing ring disposed in a first recess of the two axially-adjacent recesses and the second sealing ring disposed in a second recess of the two axially-adjacent recesses. ### Claim 10 (depends on 7) The rotor assembly of claim 7, wherein the first sealing ring and the second sealing ring axially overlap one another. ### Claim 11 (depends on 10) The rotor assembly of claim 10, wherein the inner platform surface of the platform includes a recess extending axially between the first mount and the second mount, the first sealing ring and the second sealing ring disposed in the recess. ### Claim 12 A compressor for a gas turbine engine, the compressor comprising: a stator assembly comprising at least one circumferential row of stator vanes; a rotor assembly configured to rotate relative to the stator assembly about a longitudinal centerline of the gas turbine engine, the rotor assembly comprising: a rotor disk comprising a first rotor attachment member comprising a first mount slot and a second rotor attachment member comprising a second mount slot, the rotor disk further comprising an outer diameter surface extending between the first rotor attachment member and the second rotor attachment member; a rotor blade comprising an airfoil, a platform, a first mount retained within the first mount slot, and a second mount retained within the second mount slot, the platform comprising an inner platform surface facing the outer diameter surface of the rotor disk, wherein the rotor disk and the rotor blade define a circumferential portion of a circumferentially-extending cavity between the inner platform surface, the outer diameter surface of the rotor disk, the first rotor attachment member, and the second rotor attachment member; and a seal disposed within the circumferentially-extending cavity, the seal comprising at least one sealing ring disposed about the rotational axis, the at least one sealing ring in contact with the inner platform surface of the platform and radially spaced from the outer diameter surface of the rotor disk; wherein each of the first rotor attachment member and the second rotor attachment member extend radially outward from the outer diameter surface of the rotor disk to respective first and second distal ends adjacent the inner platform surface of the platform, wherein the first mount slot and the second mount slot extend a first radial distance from the respective first and second distal ends toward the outer diameter surface of the rotor disk, and wherein the first mount slot and the second mount slot are spaced from the outer diameter surface of the rotor disk by a second radial distance. ### Claim 13 (depends on 12) The compressor of claim 12, wherein the at least one sealing ring comprises a first sealing ring and a second sealing ring axially adjacent the first sealing ring. ### Claim 14 A method for assembling a rotor assembly for a piece of rotational equipment, the method comprising: radially inserting a rotor blade into a rotor disk comprising a first rotor attachment member comprising a first mount slot and a second rotor attachment member comprising a second mount slot, the rotor disk further comprising an outer diameter surface extending between the first rotor attachment member and the second rotor attachment member; and axially inserting a first mount of the rotor blade into the first mount slot and a second mount of the rotor blade into the second mount slot, the rotor blade comprising an airfoil and a platform comprising an inner platform surface facing the outer diameter surface; wherein the rotor disk and the rotor blade define a circumferential portion of a circumferentially-extending cavity between the inner platform surface, the outer diameter surface, the first rotor attachment member, and the second rotor attachment member, the method further comprising: inserting a seal into the circumferentially-extending cavity before the step of radially inserting the rotor blade into the rotor disk, the seal comprising a first sealing ring and a second sealing ring axially adjacent the first sealing ring within the circumferentially-extending cavity. ### Claim 15 (depends on 14) The method of claim 14, further comprising axially and radially compressing the first sealing ring and the second sealing ring after the step of inserting the seal into the circumferentially-extending cavity and before the step of radially inserting the rotor blade into the rotor disk.