# US 11,441,442 B2 · Device for sealing between a rotor and a stator of 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 11,441,442 B2 - Document ID: US11441442B2 - Status: Granted - Kind: B2 - Application number: 16/608,103 - Filed: 2018-04-24 - Published: 2020-03-26 - Granted: 2022-09-13 - Earliest claimed: 2017-04-24 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Baptiste Marie Aubin Pierre Jouy; Josselin Luc Florent Sicard; Mathieu Charles Jean Verdiere; Loïc Fabien François Villard - Web page: https://patentgrep.com/patent/US11441442B2 ## CPC - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 11/122: {with erodable or abradable material (blades having cutting or grinding tips F01D5/20)} - F01D 5/225: {by shrouding} - F01D 11/02: by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) - F05D 2240/55: Seals - F05D 2250/283: honeycomb - F05D 2300/611: Coating - 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 sealing device between a rotor part and a stator part, including at least one abradable coating cooperating with at least two upstream and downstream labyrinth seal lips. Axially upstream of the labyrinth seal lips, the sealing device includes a circumferential wall that radially extends beyond the upstream free axial sealing surface of the coating to create, at the free end of the upstream labyrinth seal lip, a separation of the circulating gas. ## Claims ### Claim 1 A sealing device arranged to cooperate with a rotor part and a stator part, both of an aircraft gas turbomachine in which a gas stream is to circulate from upstream to downstream, the rotor part being adapted to rotate relative to the stator part about an axis, the sealing device comprising: two labyrinth seal lips, respectively an upstream one and a downstream one, both being elements of the rotor part; and, at least one block made of an abradable material: attached to the stator part, and adapted to cooperate with said two labyrinth seal lips, each projecting radially to said axis over an end portion of the rotor part, the at least one block has, radially to said axis, a first upstream free axial sealing surface and a downstream free axial sealing surface, and said two labyrinth seal lips have, radially to said axis, respective free ends, the free end of the downstream labyrinth seal lip and the downstream free axial sealing surface being located at positions radial to said axis which are each further from the axis than the free end of the upstream labyrinth seal lip and the first upstream free axial sealing surface, wherein, upstream of said two labyrinth seal lips, the sealing device comprises a circumferential wall which extends radially to said axis upstream and adjacent to the first upstream free axial sealing surface of said at least one block, by penetrating radially to said axis into the gas stream, and wherein: the sealing device further has a second upstream free axial sealing surface which is adjacent to said circumferential wall, upstream of the circumferential wall, and, the circumferential wall projects radially with respect to the first upstream free axial sealing surface and second upstream free axial sealing surface of the sealing device, and wherein said first upstream free axial sealing surface and downstream free axial sealing surface have a radial connection wall between them, and: 1≤D1/D2≤1.5, or 1≤L2/L1≤4, or 1≤L3/L1≤3, wherein: D1 is a radial distance between the first upstream free axial sealing surface of said at least one block and the free end of the circumferential wall, D2 is a radial distance between the free end of the circumferential wall and a radially outer face of an upstream facing spoiler, L1 is an axial thickness of the upstream labyrinth seal lip, at the free end, L2 is an axial distance between a downstream face of the circumferential wall and an upstream face, at the free end, of the upstream labyrinth seal lip, and L3 is an axial distance between a downstream face, at the free end, of the upstream labyrinth seal lip and the radial connecting wall. ### Claim 2 (depends on 1) The device according to claim 1 wherein, radially to said axis, the circumferential wall extends axially opposite a part of the upstream labyrinth seal lip located radially to said axis at a distance from the free end of said upstream labyrinth seal lip. ### Claim 3 (depends on 1) The device according to claim 1, wherein the circumferential wall is axially located at or towards an upstream end of the first upstream free axial sealing surface of the at least one block. ### Claim 4 (depends on 2) The device according to claim 2, wherein the circumferential wall is axially located at or towards an axially upstream end of the first upstream free axial sealing surface of the at least one block. ### Claim 5 (depends on 2) The device according to claim 2, wherein the circumferential wall is integral with said at least one block. ### Claim 6 (depends on 2) The device according to claim 2, wherein the circumferential wall is formed on said at least one block. ### Claim 7 (depends on 1) The device according to claim 1, wherein the upstream labyrinth seal lip is inclined towards said first upstream free axial sealing surface, upstream with respect to the axis and to a direction radial to the axis, over at least a part of a length of the upstream labyrinth seal lip. ### Claim 8 (depends on 2) The device according to claim 2, wherein the upstream labyrinth seal lip is inclined towards said first upstream free axial sealing surface, upstream with respect to the axis and to a direction radial to the axis, over at least a part of a length of the upstream labyrinth seal lip. ### Claim 9 (depends on 1) The device according to claim 1 wherein said first upstream free axial sealing surface and downstream free axial sealing surface have a radial connection wall between them. ### Claim 10 (depends on 1) The device according to claim 1, wherein: the at least one block has a cellular structure comprising radial cells individually having an axial dimension, and the circumferential wall has an axial thickness greater than said axial dimension of the cells located on the same circumference, transversely to said axis. ### Claim 11 (depends on 1) The device according to claim 1, wherein: the end portion of the rotor part over which said two labyrinth seal lips radially project comprises a platform provided at an upstream end with the upstream facing spoiler, and radially to the axis, the circumferential wall extends opposite, but at a distance from, the upstream facing spoiler. ### Claim 12 (depends on 1) A gas turbomachine for an aircraft, wherein it is equipped with the sealing device according to claim 1. ### Claim 13 (depends on 3) The device according to claim 3, wherein: the end portion of the rotor part over which said two labyrinth seal lips radially project comprises a platform provided at the upstream end with an upstream facing spoiler, and radially to the axis, the circumferential wall extends opposite, but at a distance from, the spoiler. ### Claim 14 (depends on 3) The device according to claim 3, wherein the free end of the upstream labyrinth seal lip is located radially opposite an axially upstream part of the first upstream free axial sealing surface. ### Claim 15 (depends on 1) The device according to claim 1, wherein the circumferential wall projects radially with respect to the first upstream free axial sealing surface of the sealing device, which the first upstream free axial sealing surface is adjacent to the circumferential wall, axially, upstream of the circumferential wall. ### Claim 16 A sealing device arranged to cooperate with a rotor part and a stator part, both of an aircraft gas turbomachine in which a gas stream is to circulate from upstream to downstream, the rotor part being adapted to rotate relative to the stator part about an axis, the sealing device comprising: two labyrinth seal lips, respectively an upstream one and a downstream one, both being elements of the rotor parts, and, at least one block made of an abradable material: attached to the stator part, and adapted to cooperate with said two labyrinth seal lips, each projecting radially to said axis over an end portion of the rotor part, the at least one block has, radially to said axis, an upstream free axial sealing surface and a downstream free axial sealing surface, and said two labyrinth seal lips have, radially to said axis, respective free ends, the free end of the downstream labyrinth seal lip and the downstream free axial sealing surface being located at positions radial to said axis which are each further from the axis than the free end of the upstream labyrinth seal lip and the upstream free axial sealing surface, wherein, upstream of said two labyrinth seal lips, the sealing device comprises a circumferential wall which extends radially to said axis beyond the upstream free axial sealing surface of said at least one block, by penetrating radially to said axis into the gas stream, and wherein: the end portion of the rotor part over which said two labyrinth seal lips radially project comprises a platform provided at an upstream end with an upstream facing spoiler, and radially to the axis, the circumferential wall extends opposite, but at a distance from, the upstream facing spoiler, wherein the circumferential wall projects radially with respect to the upstream free axial sealing surface of the sealing device, which the upstream free axial sealing surface is adjacent to the circumferential wall, axially, upstream of the circumferential wall; wherein said upstream free axial sealing surface and downstream free axial sealing surface have a radial connection wall between them, and: 1≤D1/D2≤1.5, 1≤L2/L1≤4, 1≤L3/L1≤3, wherein D1 is a radial distance between the upstream free axial sealing surface of said at least one block and the free end of the circumferential wall, D2 is a radial distance between the free end of the circumferential wall and a radially outer face of the upstream facing spoiler, L1 is an axial thickness of the upstream labyrinth seal lip 40a, at the free end, L2 is an axial distance between a downstream face of the circumferential wall and an upstream face, at the free end, of the upstream labyrinth seal lip, and L3 is an axial distance between a downstream face, at the free end, of the upstream labyrinth seal lip and the radial connecting wall.