# US 8,739,552 B2 · Structural nacelle > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,739,552 B2 - Document ID: US8739552B2 - Status: Granted - Kind: B2 - Application number: 12/302,998 - Filed: 2007-06-11 - Published: 2009-10-15 - Granted: 2014-06-03 - Earliest claimed: 2006-06-30 - Assignees: Aircelle - Applicants: Guy Bernard Vauchel; Anne-Laure Gibouin; Regis Fassier; Jean-Philippe Joret; Jerome Collier; Guillaume Lefort; Pierre-Alain Chouard - Inventors: Guy Bernard Vauchel; Anne-Laure Gibouin; Regis Fassier; Jean-Philippe Joret; Jerome Collier; Guillaume Lefort; Pierre-Alain Chouard - Web page: https://patentgrep.com/patent/US8739552B2 ## CPC - B64D 29/00: Power-plant nacelles, fairings or cowlings - B64D 27/18: within, or attached to, wings - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT ## Abstract The present invention relates, on the one hand, to a nacelle (1) for a double flow turboreactor (2) comprising a front air intake section (5), a median section (6) intended for surrounding a fan (3) of the turboreactor and a rear section (7), said rear section having an internal structure (7b) intended for serving as a housing to a rear portion of the turboreactor, characterized in that the internal structure possesses attachment means suitable for enabling the nacelle to be fastened to a pylon (12) intended to be connected to a fixed structure (13) of an aeroplane on at least one portion of said internal structure, and on the other hand, to a propellant assembly and to an aircraft provided with such a nacelle. ## Claims ### Claim 1 A nacelle for a turbofan comprising a front air intake section, a mid-section designed to surround a fan of a turbojet and a rear section, said rear section having an internal structure designed to serve as a casing to rear portion of the turbojet and an external structure, wherein the internal structure has coupling means suitable for allowing an attachment of the nacelle to a pylon designed to be connected to a fixed structure of an aircraft on at least one portion of said internal structure, wherein the internal structure comprises at least one external wall forming an aerodynamic surface adjacent a cold flow stream that flows between the internal structure and the external structure, the external wall mounted over a framework made from plurality of radial frames distributed over the length of the internal structure and each radial frame comprising a circumferential ring, wherein each adjacent circumferential ring is connected together by at least one reinforcement between them. ### Claim 2 (depends on 1) The nacelle as claimed in claim 1, wherein the internal structure is fitted with means for rigid connection to the turbojet. ### Claim 3 (depends on 1) The nacelle as claimed in claim 1, wherein the internal structure is connected to the mid-section by means of a casing surrounding the fan. ### Claim 4 (depends on 3) The nacelle as claimed in claim 3, wherein the internal structure is connected to the mid-section of the downstream portion of the casing surrounding the fan on at least a portion of its periphery. ### Claim 5 (depends on 4) The nacelle as claimed in claim 4, wherein the internal structure is connected to the mid-section of the downstream portion of the casing over the whole of its periphery. ### Claim 6 (depends on 4) The nacelle as claimed in claim 4, wherein the peripheral groove of the casing has a V-shaped internal profile. ### Claim 7 (depends on 6) The nacelle as claimed in claim 6, wherein the framework comprises at least one longitudinal reinforcement on either side of a longitudinal axis of the internal structure. ### Claim 8 (depends on 1) The nacelle as claimed in claim 1, wherein the internal structure is fitted with a means for recentering the turbojet. ### Claim 9 (depends on 1) The nacelle as claimed in claim 1, wherein the internal structure is designed so that the pylon can extend over the whole length of the internal structure. ### Claim 10 (depends on 1) The nacelle as claimed in claim 1, wherein the pylon is incorporated into the internal structure. ### Claim 11 (depends on 1) The nacelle as claimed in claim 1, wherein the framework totally surrounds the turbojet. ### Claim 12 (depends on 1) The nacelle as claimed in claim 1, wherein the external wall is partially or totally made from at least one acoustic panel. ### Claim 13 (depends on 1) The nacelle as claimed in claim 1, wherein the radial frames are made from force-absorbing link rods. ### Claim 14 (depends on 1) The nacelle as claimed in claim 1, wherein at least a portion of the radial frames are made in a single piece. ### Claim 15 (depends on 1) The nacelle as claimed in claim 1, wherein at least a portion of the radial frames are made from several elements linked together, for example by bolting. ### Claim 16 (depends on 1) The nacelle as claimed claim 1, wherein the framework comprises at least one front radial frame and one rear radial frame connected by an intermediate structure forming a mesh. ### Claim 17 (depends on 16) The nacelle as claimed in claim 16, wherein the intermediate structure is made in the form of a caisson. ### Claim 18 (depends on 16) The nacelle as claimed in claim 16, wherein the intermediate structure is made from link bars connecting at least two radial frames together. ### Claim 19 (depends on 18) The nacelle as claimed in claim 18, wherein at least a portion of the link bars are incorporated into at least one radial frame. ### Claim 20 (depends on 18) The nacelle as claimed in claim 18, wherein the link bars are hollow. ### Claim 21 (depends on 18) The nacelle as claimed in claim 18, wherein the link bars are placed relative to one another so as to form triangles, preferably isosceles triangles. ### Claim 22 (depends on 1) The nacelle as claimed in claim 1, wherein the internal structure comprises at least one link rod for absorbing thrust attached to at least one point of an upstream portion of the internal structure and at least one point of a downstream portion of the internal structure in the vicinity of the pylon or optionally incorporated into the latter. ### Claim 23 (depends on 22) The nacelle as claimed in claim 22, wherein the link rod for absorbing thrust is oriented substantially in the structural alignment of the pylon. ### Claim 24 (depends on 22) The nacelle as claimed in claim 22, wherein the link rod for absorbing thrust has a fork attached to the internal structure at at least two points of the upstream portion of the internal structure, on either side of the horizontal mid-plane, the fork of the link rod having a junction point situated at a radial frame of the framework. ### Claim 25 (depends on 1) The nacelle as claimed in claim 1, wherein at least one portion of the framework elements comprising at least one of the radial frames, force-absorbing link rods, intermediate structure and longitudinal reinforcements, are fitted with a heat protection. ### Claim 26 (depends on 1) The nacelle as claimed in claim 1, wherein the internal structure has a one-piece framework. ### Claim 27 (depends on 1) The nacelle as claimed in claim 1, wherein the internal structure has a two-piece framework designed to be assembled substantially vertically. ### Claim 28 (depends on 1) A propulsion system, comprising a nacelle as claimed in claim 1, said nacelle accommodating a turbo-jet. ### Claim 29 (depends on 28) An aircraft, comprising at least one propulsion system as claimed in claim 28.