# US 12,760,684 B2 · Aircraft turbine engine assembly comprising a holder for fittings > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,760,684 B2 - Document ID: US12760684B2 - Status: Granted - Kind: B2 - Application number: 18/257,830 - Filed: 2021-12-15 - Published: 2024-02-15 - Granted: 2026-10-13 - Earliest claimed: 2020-12-15 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Bruno Albert Beutin; Anthony Pierre Guy Delaforge; Zoltan Zsiga - Web page: https://patentgrep.com/patent/US12760684B2 ## CPC - F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - 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) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) ## Abstract Assembly for an aircraft turbine engine, comprising an intermediate casing hub, an accessory gearbox, and a transfer case including a power transmission shaft configured to transmit mechanical power, taken off an engine shaft of the turbine engine, to at least one accessory mounted on the accessory gearbox, in which the transfer case comprises a structural element surrounding the power transmission shaft and rigidly attaching the accessory gearbox to the intermediate casing hub. ## Claims ### Claim 1 An assembly for an aircraft turbine engine comprising an intermediate casing hub, an accessory gearbox, and a transfer case including a power transmission shaft configured to transmit mechanical power, taken off an engine shaft of the aircraft turbine engine, to at least one accessory mounted on the accessory gearbox, wherein the transfer case comprises a reinforced structural element surrounding the power transmission shaft and rigidly attaching the accessory gearbox to the intermediate casing hub, the assembly further comprising two arms connecting the accessory gearbox to the intermediate casing hub, the two arms being provided on both sides of the reinforced structural element, wherein the intermediate casing hub includes two or more openings, each of the two or more openings configured to allow a passage of discharge outlets of a compressor, and wherein each of the two arms is provided between successive openings. ### Claim 2 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein the accessory gearbox is formed by a housing which has an upstream face located downstream of the intermediate casing hub, and the reinforced structural element is rigidly attached to said upstream face. ### Claim 3 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, the assembly being bereft of other attachment between the accessory gearbox and the intermediate casing hub than the reinforced structural element and said two arms. ### Claim 4 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein at least one of the two arms is attached to at least one of the intermediate casing hub and the accessory gearbox in an articulated manner so as to transfer forces only in tension. ### Claim 5 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein the reinforced structural element is formed by an envelope of the transfer case. ### Claim 6 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein the power transmission shaft extends substantially perpendicular to an upstream face of the accessory gearbox. ### Claim 7 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, comprising the at least one accessory mounted on an upstream face of the accessory gearbox, said at least one accessory having an axial dimension smaller than a distance between said upstream face and a downstream annular flange of the intermediate casing hub. ### Claim 8 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein an attachment of the accessory gearbox to the intermediate casing hub is statically determinate. ### Claim 9 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein the intermediate casing hub comprises a downstream annular flange to which the reinforced structural element is attached, and the transfer case comprises an angle gearbox located in the intermediate casing hub upstream of the downstream annular flange, said angle gearbox connecting the power transmission shaft to the engine shaft of the aircraft turbine engine by means of a radial shaft of the aircraft turbine engine. ### Claim 10 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein the accessory gearbox is attached to the intermediate casing hub so as to be positioned, in an operating position, mostly below an axis of the intermediate casing hub. ### Claim 11 (depends on 1) The aircraft turbine engine comprising the assembly according to claim 1. ### Claim 12 (depends on 11) The aircraft turbine engine according to claim 11 comprising, downstream of an intermediate casing having the intermediate casing hub, a compressor casing and a combustion chamber casing, and wherein the assembly is bereft of attachment between the accessory gearbox and the compressor casing as well as the combustion chamber casing. ### Claim 13 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein the intermediate casing hub comprises an annular flange, wherein the annular flange includes the two or more openings. ### Claim 14 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein the reinforced structural element is sized to be able to support a weight of the accessory gearbox and of accessories carried by the accessory gearbox, relative to the intermediate casing hub. ### Claim 15 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein the two arms are connected to a surface of the accessory gearbox that is distinct from an upstream face and a downstream face of the accessory gearbox. ### Claim 16 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein a first arm of the two arms is attached to the accessory gearbox by a first connection, wherein the first arm of the two arms is attached to the intermediate casing hub by a second connection. ### Claim 17 (depends on 16) The assembly for the aircraft turbine engine according to claim 16, wherein the first connection is a ball and socket connection, and the second connection is a flexible stud. ### Claim 18 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein the intermediate casing hub includes a downstream annular flange extending radially inward from a downstream part of a frusto-conical portion of the intermediate casing hub. ### Claim 19 (depends on 1) The assembly for the aircraft turbine engine according to claim 1, wherein the intermediate casing hub includes an upstream annular flange extending radially inward from an upstream part of a frusto-conical portion of the intermediate casing hub. ### Claim 20 An assembly for an aircraft turbine engine comprising an intermediate casing hub, an accessory gearbox, and a transfer case including a power transmission shaft configured to transmit mechanical power, taken off an engine shaft of the aircraft turbine engine, to at least one accessory mounted on the accessory gearbox, wherein the transfer case comprises a structural element surrounding the power transmission shaft and rigidly attaching the accessory gearbox to the intermediate casing hub, the assembly further comprising two arms connecting the accessory gearbox to the intermediate casing hub, the two arms being provided on both sides of the structural element, the assembly being bereft of other attachment between the accessory gearbox and the intermediate casing hub than the structural element and said two arms, wherein the intermediate casing hub includes two or more openings, each of the two or more openings configured to allow a passage of discharge outlets of a compressor, and wherein each of the two arms is provided between successive openings.