# US 12,110,803 B2 · Aircraft turbine engine assembly comprising a support for equipment > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,110,803 B2 - Document ID: US12110803B2 - Status: Granted - Kind: B2 - Application number: 18/568,168 - Filed: 2022-05-27 - Published: 2024-08-29 - Granted: 2024-10-08 - Earliest claimed: 2021-06-09 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Zoltan Zsiga; Valentin Sébastien Simon Avoyne; Matthieu Bruno François Foglia - Web page: https://patentgrep.com/patent/US12110803B2 ## CPC - F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing - 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 7/32: Arrangement, mounting, or driving, of auxiliaries - F05D 2250/312: the axes being parallel to each other - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract An assembly for an aircraft turbomachine, comprising an intermediate casing hub, an equipment support having an upstream face located downstream of the intermediate casing hub, and a transfer gear box driving a power transmission shaft configured to transmit mechanical power, taken off an engine shaft of the turbomachine, to at least one upstream equipment item mounted on the upstream face of the equipment support, the upstream equipment item comprising a structural element attaching the equipment support to the intermediate casing hub. ## Claims ### Claim 1 An assembly for an aircraft turbomachine, comprising an intermediate casing hub, an equipment support having an upstream face located downstream of the intermediate casing hub, and a transfer gear box driving a power transmission shaft configured to transmit mechanical power, taken off an engine shaft of the turbomachine, to at least one upstream equipment item mounted on the upstream face of the equipment support, the upstream equipment item comprising a structural element attaching the equipment support to the intermediate casing hub. ### Claim 2 (depends on 1) The assembly for an aircraft turbomachine as claimed in claim 1, wherein the upstream equipment item comprises a functional part, the structural element at least partly surrounding the functional part. ### Claim 3 (depends on 1) The assembly for an aircraft turbomachine as claimed in claim 1, wherein the at least one upstream equipment item is one from among an electric generator to supply electrical power to the aircraft, an alternator to supply electrical current to electrical equipment items of the turbomachine, a starter to start the turbomachine, a hydraulic pump to provide hydraulic power to the aircraft, a fuel pump, or a lubrication pump. ### Claim 4 (depends on 1) The assembly for an aircraft turbomachine as claimed in claim 1, wherein the structural element is rigidly attached to the upstream face and to the intermediate casing hub. ### Claim 5 (depends on 1) The assembly for an aircraft turbomachine as claimed in claim 1, wherein the structural element is rigidly attached to the upstream face, the assembly further comprising at least one upstream arm connecting the structural element of the upstream equipment item to the intermediate casing hub, and wherein a rigid sheath surrounds the power transmission shaft and rigidly attaches the equipment support to the intermediate casing hub. ### Claim 6 (depends on 1) The assembly for an aircraft turbomachine as claimed in claim 1, wherein the structural element is rigidly attached to the upstream face, the assembly further comprising at least one upstream arm connecting the structural element of the upstream equipment item to the intermediate casing hub, at least one downstream equipment item mounted on a downstream face of the equipment support, and at least one downstream arm configured to connect the downstream equipment item to a casing of the turbomachine disposed downstream of the equipment support. ### Claim 7 (depends on 5) The assembly for an aircraft turbomachine as claimed in claim 5, wherein the at least one upstream arm is attached to the intermediate casing hub and/or to the structural element of the upstream equipment item in an articulated manner. ### Claim 8 (depends on 1) The assembly for an aircraft turbomachine as claimed in claim 1, wherein the attachment of the equipment support to the intermediate casing hub is isostatic. ### Claim 9 (depends on 1) The assembly for an aircraft turbomachine as claimed in claim 1, wherein the equipment support is attached to the intermediate casing hub such that, in a working position, a majority of the equipment support is located below an axis of the intermediate casing hub. ### Claim 10 (depends on 1) The assembly for an aircraft turbomachine as claimed in claim 1, comprising at least two upstream equipment items, the at least two upstream equipment items each comprising a structural element and being each disposed at two opposite ends of the equipment support. ### Claim 11 (depends on 1) An aircraft turbomachine comprising an assembly as claimed in claim 1. ### Claim 12 (depends on 11) An aircraft turbomachine as claimed in claim 11, comprising, downstream of the intermediate casing, a compressor casing and a combustion chamber casing, and wherein the assembly has no attachment between the equipment support and the compressor casing as well as the combustion chamber casing.