# US 11,028,713 B2 · Rotating carbon piston ring seal > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,028,713 B2 - Document ID: US11028713B2 - Status: Granted - Kind: B2 - Application number: 16/373,876 - Filed: 2019-04-03 - Published: 2020-10-08 - Granted: 2021-06-08 - Earliest claimed: 2019-04-03 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Scot A. Webb - Web page: https://patentgrep.com/patent/US11028713B2 ## CPC - F01D 11/005: {Sealing means between non relatively rotating elements} - F16J 15/3208: provided with tension elements, e.g. elastic rings - F16J 15/3232: having two or more lips - F16J 15/3464: {Mounting of the seal} - F01D 11/025: {Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations} - F05D 2220/32: in gas turbines - F05D 2230/64: using positioning or alignment devices for aligning or centring, e.g. pins - F05D 2240/55: Seals - F05D 2240/58: Piston ring seals - F05D 2260/38: by a spring, i.e. spring loaded or biased towards a certain position - F05D 2300/224: Carbon, e.g. graphite - F16J 15/164: {the sealing action depending on movements; pressure difference, temperature or presence of leaking fluid} - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F16J: PISTONS {(specially adapted for dampers F16F9/32)}; CYLINDERS; SEALINGS - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A gas turbine engine assembly includes a compressor including a plurality of rotors, where at least one of the plurality of rotors includes a radial inner sealing surface. A rotating shaft drives rotation of the plurality of rotors, where the rotating shaft includes an annular groove proximate the radial inner sealing surface. A seal is disposed within the annular groove, and the seal comprises at least two annular sections forming a complete circumference. Each of the at least two annular sections are separate parts and include a radially-facing sealing surface engaged to the radial inner sealing surface of the rotor and an annular slot disposed radially inward of the radially-facing sealing surface. A retainer is disposed within the annular slot limiting radial expansion of the at least two annular sections. ## Claims ### Claim 1 A gas turbine engine assembly comprising: a compressor including a plurality of rotors, wherein at least one of the plurality of rotors includes a radial inner sealing surface; a rotating shaft driving rotation of the plurality of rotors, wherein the rotating shaft includes an annular groove proximate the radial inner sealing surface; and a seal disposed within the annular groove, the seal comprising at least two annular sections forming a complete circumference, wherein each of the at least two annular sections are separate parts and include a radially-facing sealing surface engaged to the radial inner sealing surface and an annular slot disposed radially inward of the radially-facing sealing surface; and a retainer disposed within the annular slot limiting radial expansion of the at least two annular sections. ### Claim 2 (depends on 1) The gas turbine engine assembly as recited in claim 1, wherein the annular slot is disposed on a radially outer side of each of the at least two annular sections. ### Claim 3 (depends on 2) The gas turbine engine assembly as recited in claim 2, wherein the radially-facing sealing surface comprises a sealing surface on axial sides of the annular slot. ### Claim 4 (depends on 1) The gas turbine engine assembly as recited in claim 1, including an overlapping interface between ends of the at least two annular sections. ### Claim 5 (depends on 4) The gas turbine engine assembly as recited in claim 4, wherein the at least two annular sections includes multiple annular sections each including an overlapping interface between adjacent ends. ### Claim 6 (depends on 1) The gas turbine engine assembly as recited in claim 1, wherein the retainer comprises a spring that exerts a biasing force radially inward on the at least two annular sections. ### Claim 7 (depends on 1) The gas turbine engine assembly as recited in claim 1, wherein each of the at least two annular sections comprises a carbon material. ### Claim 8 (depends on 1) The gas turbine engine assembly as recited in claim 1, wherein the shaft includes a section of increased diameter with the annular groove positioned within the increased diameter. ### Claim 9 (depends on 8) The gas turbine engine as recited in claim 8, wherein the radial inner surface includes an axially extending portion. ### Claim 10 (depends on 1) The gas turbine engine as recited in claim 1, wherein the seal prevents hot airflow from moving forward past the seal. ### Claim 11 A method of assembling a rotating seal for a gas turbine engine comprising: positioning at least two annular seal sections within an annular groove formed in a shaft; and holding the at least two annular seal sections within the annular groove with a retainer disposed within an annular slot of within each of the at least two annular seal sections. ### Claim 12 (depends on 11) The method as recited in claim 11, including assembling a radially inner sealing surface of a rotor radially outward of the annular groove and in sealing contact with the at least two annular sections. ### Claim 13 (depends on 12) The method as recited in claim 12, wherein the shaft and the rotor rotate together such that there is no relative rotation there between and the seal expands radially outward against the radially inner sealing surface of the rotor in response to rotation. ### Claim 14 (depends on 13) The method as recited in claim 13, including overlapping adjacent ends of each of the at least two annular sections to maintain a complete annular seal with the seal in a radially expanded position.