# US 12,006,054 B2 · Aircraft nacelle inlet > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,006,054 B2 - Document ID: US12006054B2 - Status: Granted - Kind: B2 - Application number: 17/766,852 - Filed: 2020-10-14 - Published: 2023-06-29 - Granted: 2024-06-11 - Earliest claimed: 2019-10-15 - Assignees: Safran Nacelles - Applicants: Safran Nacelles Limited - Inventors: David Kirk; Graeme Hill; David Hebden; Simon Furmston - Web page: https://patentgrep.com/patent/US12006054B2 ## CPC - B64D 33/02: of combustion air intakes - B64D 29/00: Power-plant nacelles, fairings or cowlings - F02C 7/045: having provisions for noise suppression - B64D 2033/0206: {comprising noise reduction means, e.g. acoustic liners} - B64D 2033/0233: {comprising de-icing means} - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An aircraft nacelle air inlet comprising: a lip skin defining a curved surface of the inlet, the curved surface extending about a longitudinal axis of the inlet; a forward bulkhead; an inner barrel having a radially inner surface defining a surface of the inlet, a radially outer surface, and a sound attenuating layer arranged between the radially inner and radially outer surfaces; and a joining frame fixed to the lip skin and/or to the forward bulkhead. A first portion of the joining frame extends over at least a portion of the sound attenuating layer of the inner barrel and is fixed to the radially outer surface of the inner barrel. ## Claims ### Claim 1 An air inlet for an aircraft nacelle, the air inlet comprising: a lip skin defining a curved surface of the inlet, the curved surface extending about a longitudinal axis of the inlet; a forward bulkhead; an inner barrel having a radially inner surface defining a surface of the inlet, a radially outer surface, and a sound attenuating layer arranged between the radially inner and radially outer surfaces; and a joining frame fixed to the lip skin and/or to the forward bulkhead; wherein a first portion of the joining frame extends over at least a portion of the sound attenuating layer of the inner barrel and is fixed to the radially outer surface of the inner barrel, wherein a second portion of the joining frame is substantially perpendicular to the first portion and defines a flat surface extending over an end surface of the inner barrel, wherein the joining frame further comprises a third portion, the third portion extending over at least a portion of the forward bulkhead, and wherein the third portion extends from the first portion and the second portion, wherein the joining frame is Y-shaped as viewed in cross-section, and the first, second and third portions of the joining frame respectively constitute three different legs of the Y-shape. ### Claim 2 (depends on 1) The air inlet of claim 1, wherein the inner barrel has an end surface substantially perpendicular to at least one of the radially outer surface and the radially inner surface. ### Claim 3 (depends on 1) The air inlet of claim 1, wherein the joining frame further comprises a fourth portion, the fourth portion being a joining frame curved surface extending over at least a portion of the lip skin. ### Claim 4 (depends on 3) The air inlet of claim 3, wherein the first portion of the joining frame is formed integrally with at least one of the second, third, and fourth portions. ### Claim 5 (depends on 1) The air inlet of claim 1, wherein the lip skin has a flat surface extending radially outwardly from the curved surface and at least a portion of the flat surface of the lip skin overlaps the joining frame. ### Claim 6 (depends on 1) The air inlet of claim 1, wherein the lip skin and the bulkhead together define a compartment. ### Claim 7 (depends on 1) The air inlet of claim 1, wherein the lip skin comprises a structural sheet defining the curved surface and a lip skin sound attenuating layer arranged on a radially outer side of the structural sheet. ### Claim 8 (depends on 7) The air inlet of claim 7, wherein the lip skin further comprises a further structural sheet on a radially outer surface of the lip skin sound attenuating layer, the further structural sheet being fixed to the joining frame. ### Claim 9 (depends on 8) The air inlet of claim 8, further comprising a second joining frame, the second joining frame being coupled to the further structural sheet and to the structural sheet of the lip skin. ### Claim 10 (depends on 9) The air inlet of claim 9, wherein at least one of the joining frame and the second joining frame is annular. ### Claim 11 (depends on 10) The air inlet of claim 10, wherein at least one of the joining frame and the second joining frame is formed of multiple parts, each part being a sector of an annulus. ### Claim 12 (depends on 11) The air inlet of claim 11, further comprising ventilation holes through the lip skin, the ventilation holes arranged forward of the joining frame and configured to vent hot gas for heating a radially inner surface of the inlet. ### Claim 13 (depends on 1) The air inlet of claim 1, wherein the inner barrel comprises a radially inner structural sheet defining the radially inner surface and a radially outer structural sheet defining the radially outer surface, the sound attenuating layer being disposed between the radially inner and radially outer structural sheets. ### Claim 14 An aircraft nacelle comprising: a fan casing; and an air inlet secured to the fan casing and comprising: a lip skin defining a curved surface of the inlet, the curved surface extending about a longitudinal axis of the inlet; a forward bulkhead; an inner barrel having a radially inner surface defining a surface of the inlet, a radially outer surface, and a sound attenuating layer arranged between the radially inner and radially outer surfaces; and a joining frame fixed to the lip skin and/or to the forward bulkhead; wherein a first portion of the joining frame extends over at least a portion of the sound attenuating layer of the inner barrel and is fixed to the radially outer surface of the inner barrel, wherein a second portion of the joining frame is substantially perpendicular to the first portion and defines a flat surface extending over an end surface of the inner barrel, wherein the joining frame further comprises a third portion, the third portion extending over at least a portion of the forward bulkhead, and wherein the third portion extends from the first portion and the second portion, wherein the joining frame is Y-shaped as viewed in cross-section, and the first, second and third portions of the joining frame respectively constitute three different legs of the Y-shape. ### Claim 15 (depends on 10) The air inlet of claim 10, wherein at least one of the joining frame and the second joining frame is formed of two semi-annular parts, each semi-annular part being a sector of an annulus.