# US 2024/0200464 A1 · Assembly for a turbine engine fan case and an air inlet, method for using such an assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2024/0200464 A1 - Document ID: US20240200464A1 - Status: Published application - Kind: A1 - Application number: 18/555,279 - Filed: 2022-06-02 - Published: 2024-06-20 - Earliest claimed: 2021-06-10 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Clement Raphael Laroche; Ulrich Vincent Max Dubois; Kevin Emilien Andre Minjot; Vincent Fameau - Web page: https://patentgrep.com/patent/US20240200464A1 ## CPC - F01D 11/122: {with erodable or abradable material (blades having cutting or grinding tips F01D5/20)} - F01D 7/00: Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) - F05D 2220/36: specially adapted for the fan of turbofan engines - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An assembly for a turbine engine fan case and an air inlet, in particular for an aircraft. The turbine engine extending along a longitudinal axis and comprising at least one fan mounted so as to be rotatable about the longitudinal axis. The fan case comprising at least a first peripheral lining. The first peripheral lining being made of an abradable material configured to be capable of being worn out during the rotation of the fan. The air inlet comprising at least one second peripheral lining. The second peripheral lining being made of an abradable material configured to be capable of being worn out during the rotation of the fan. ## Claims ### Claim 1 An assembly of an engine fan case and a nacelle air inlet for a turbine engine, the turbine engine extending along a longitudinal axis and comprising at least one fan mounted so as to be rotatable about the longitudinal axis, the fan case comprising at least one first peripheral lining, the first peripheral lining being made of an abradable material configured to be capable of being worn out during the rotation of the fan, wherein the nacelle air inlet comprises at least one second peripheral lining, the second peripheral lining being made of an abradable material configured to be capable of being worn out during the rotation of the fan. ### Claim 2 (depends on 1) The assembly according to claim 1, wherein the first peripheral lining and the second peripheral lining are made of a same abradable material. ### Claim 3 (depends on 1) The assembly according to claim 1, wherein the fan case and the air inlet are joined together, and wherein the first peripheral lining and the second peripheral lining are adjacent one another. ### Claim 4 (depends on 1) The assembly according to claim 1, wherein the first peripheral lining extends to an upstream end of the fan case. ### Claim 5 (depends on 1) The assembly according to claim 1, wherein the second peripheral lining extends to a downstream end of the air inlet. ### Claim 6 (depends on 1) The assembly according to claim 1, wherein the first peripheral lining defines a first length and the second peripheral lining defines a second length, and wherein a ratio of the second length to the first length is greater than 20%. ### Claim 7 (depends on 1) A turbine engine for an aircraft, the turbine engine comprising: the fan case and the air inlet according to claim 1, the turbine engine extending along the longitudinal axis and comprising the at least one fan mounted so as to be rotatable about the longitudinal axis configured to come into contact with at least one of the peripheral linings. ### Claim 8 (depends on 7) The turbine engine according to claim 7, wherein the fan comprises variable-pitch blades. ### Claim 9 (depends on 7) The turbine engine according to claim 7, the fan defines a first pitch angle corresponding to an operation of the turbine engine in direct flow, and the fan is configured to be able to come into contact only with the first peripheral lining for the first pitch angle. ### Claim 10 (depends on 7) The turbine engine according to one of claim 7, the fan defines a second pitch angle corresponding to reverse flow operation of the turbine engine, and wherein the fan is configured to be able to come into contact with the second peripheral lining for the second pitch angle. ### Claim 11 (depends on 1) The assembly according to claim 1, the fan case comprising at an upstream end thereof an upstream fastening member, wherein the air inlet comprises at a downstream end thereof a downstream fastening member configured to cooperate with the upstream fastening member of the fan case. ### Claim 12 (depends on 7) A method for using the turbine engine according to claim 7, comprising a step of rotating the fan during which blades of the fan come into contact with at least one of the first peripheral lining and the second peripheral lining. ### Claim 13 (depends on 12) The method for using the turbine engine according to claim 12, wherein the blades of the fan comprise variable-pitch blades, the method comprising: rotating the fan for a first pitch angle of blades during which blades come into contact only with the first peripheral lining, and rotating the fan for a second pitch angle of blades during which blades come into contact with the second peripheral lining. ### Claim 14 (depends on 1) The assembly according to claim 1, wherein the first peripheral lining defines a first length and the second peripheral lining defines a second length, and wherein a ratio of the second length to the first length is greater than 30%. ### Claim 15 (depends on 1) The assembly according to claim 1, wherein the first peripheral lining defines a first length and the second peripheral lining defines a second length, and wherein a ratio of the second length to the first length is greater than 50%.