# US 12,215,629 B2 · Turbine engine including transfer gearbox and accessory gearbox > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,215,629 B2 - Document ID: US12215629B2 - Status: Granted - Kind: B2 - Application number: 18/184,937 - Filed: 2023-03-16 - Published: 2024-08-08 - Granted: 2025-02-04 - Earliest claimed: 2023-02-06 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: John Carl Glessner; John Robert Holland; Efren Souza Chavez; Ethan Patrick O'Connor - Web page: https://patentgrep.com/patent/US12215629B2 ## CPC - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - 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) - F02K 3/06: with front fan - F05D 2220/32: in gas turbines - F05D 2220/76: an electrical generator - F05D 2260/40: Transmission of power - 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) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A turbine engine having an engine core that includes a compressor section, a combustion section, and a turbine section. An inner cowl circumscribes the engine core and an outer cowl radially spaced from the inner cowl, circumscribes at least a portion of the inner cowl. A transfer gearbox, at least partially located within an inner cowl space between the engine core and the inner cowl, operably couples to a first accessory device. An accessory gearbox located in the outer cowl operably couples to the transfer gearbox and a second accessory device. ## Claims ### Claim 1 A turbine engine comprising: a fan section, a compressor section, a combustion section, and a turbine section in axial flow arrangement and defining a turbine engine axis of rotation, wherein the compressor section comprises a low-pressure compressor and a high-pressure compressor; an engine core defined by the compressor section, the combustion section, and the turbine section; an inner cowl circumscribing at least a portion of the engine core and radially spaced from the engine core to define an inner cowl space; an outer cowl circumscribing at least a portion of the inner cowl and spaced from the inner cowl; a transfer gearbox at least partially located in the inner cowl space; a first accessory device at least partially located in the inner cowl space and operably coupled to the transfer gearbox, wherein the first accessory device is located upstream of the combustion section; an accessory gearbox located in the outer cowl; a connection assembly operably coupling the accessory gearbox to the transfer gearbox, the connection assembly comprising: a first transfer shaft extending from the transfer gearbox to a first interface, the first transfer shaft having a first shaft centerline forming a first angle from the turbine engine axis of rotation when viewed from a plane containing both the first shaft centerline and the turbine engine axis of rotation, wherein the first angle is greater than 0° and less than 90° ; and a second transfer shaft extending from the accessory gearbox and coupled to a second interface rotatably driven by the first interface, wherein the second transfer shaft includes a second shaft centerline forming a second angle from the first shaft centerline when viewed from a plane containing both the second shaft centerline and the first shaft centerline, wherein the second angle is greater than 0° and less than 180°; a second accessory device operably coupled to the accessory gearbox and located in the outer cowl, wherein the second accessory device is upstream of the combustion section; and a heat exchanger located radially within the inner cowl space, wherein at least a portion of the heat exchanger axially overlaps a portion of a fan casing. ### Claim 2 (depends on 1) The turbine engine of claim 1, further comprising a strut extending between the inner cowl and the outer cowl, wherein the strut has a hollow interior and a first transfer shaft extends from the transfer gearbox, through the hollow interior, and into the outer cowl. ### Claim 3 (depends on 2) The turbine engine of claim 2, wherein a portion of the first accessory device extends past the inner cowl into the strut. ### Claim 4 (depends on 3) The turbine engine of claim 3, wherein the first accessory device includes an accessory thickness measured radially across the first accessory device, and an extension length measured from an outside face of the inner cowl to a farthest extent of the first accessory device, wherein a ratio of the accessory thickness to the extension length is in a range from 100:99 to 100:1. ### Claim 5 (depends on 3) The turbine engine of claim 3, wherein the strut is defined, at least in part, by strut sidewalls, wherein at least one strut sidewall of the strut sidewalls includes at least one contour or bend. ### Claim 6 (depends on 5) The turbine engine of claim 5, wherein the at least one contour or bend accommodates the portion of the first accessory device extending into the strut. ### Claim 7 (depends on 1) The turbine engine of claim 1, wherein the first accessory device is an aircraft accessory. ### Claim 8 (depends on 7) The turbine engine of claim 7, wherein the first accessory device is an electrical generator located downstream of the fan section. ### Claim 9 (depends on 1) The turbine engine of claim 1, wherein the heat exchanger is upstream of the first accessory device. ### Claim 10 (depends on 1) The turbine engine of claim 1, wherein the first accessory device is a set of first accessory devices that include one or more of an electrical generator, a hydraulic pump, primary lubrication pump, secondary lubrication pump, aircraft permanent magnet alternator, main fuel pump, fuel boost pump, fuel pump, air turbine starter, or rotisserie. ### Claim 11 (depends on 10) The turbine engine of claim 10, wherein the set of first accessory devices includes at least three accessory devices, wherein the at least three accessory devices are aircraft accessories, engine accessories, or a combination thereof. ### Claim 12 (depends on 1) The turbine engine of claim 1, wherein the second accessory device is a set of second accessory devices including one or more of a fuel pump, a lubrication pump, an air compressor, an air turbine starter, a scavenge pump, a fuel control, a permanent magnet alternator, auxiliary oil pump, starter, a hydraulic pump, primary lubrication pump, secondary lubrication pump, main fuel pump, fuel boost pump, or rotisserie. ### Claim 13 (depends on 12) The turbine engine of claim 12, wherein at least a subset of the set of second accessory devices are located upstream of the accessory gearbox. ### Claim 14 (depends on 1) The turbine engine of claim 1, wherein the fan section includes fan blades rotatable about the turbine engine axis of rotation and circumscribed by a fan casing defined, in part, by the outer cowl, wherein the accessory gearbox and the second accessory device are coupled to an exterior of the fan casing. ### Claim 15 (depends on 14) The turbine engine of claim 14, wherein the second accessory device axially overlaps the fan casing. ### Claim 16 (depends on 15) The turbine engine of claim 15, wherein the first accessory device is an electrical generator located downstream of the fan section. ### Claim 17 (depends on 1) The turbine engine of claim 1, wherein the transfer gearbox and the accessory gearbox are circumferentially spaced. ### Claim 18 (depends on 1) The turbine engine of claim 1, wherein the first interface rotatably couples to the second interface on the outer cowl. ### Claim 19 (depends on 1) The turbine engine of claim 1, further comprising at least one additional heat exchanger. ### Claim 20 (depends on 1) The turbine engine of claim 1, wherein the heat exchanger is in communication with the first accessory device via at least one line, wherein the at least one line is a conduit, tubing, piping, wiring, or other known fluid or electrical connection.