# US 11,993,387 B2 · Gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,993,387 B2 - Document ID: US11993387B2 - Status: Granted - Kind: B2 - Application number: 17/940,046 - Filed: 2022-09-08 - Published: 2023-06-01 - Granted: 2024-05-28 - Earliest claimed: 2021-09-08 - Assignees: ROLLS-ROYCE plc - Applicants: ROLLS-ROYCE plc - Inventors: Jamie W Gallagher; Daniel Blacker; Hugh J Blakemore; Adrian M Manser; Jonathan V Watson; Alexander L Fry; Robert A Barker; James Thorp; Marie-Océane Parent - Web page: https://patentgrep.com/patent/US11993387B2 ## CPC - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - B64D 27/33: Hybrid electric aircraft - B64D 27/402: {comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant} - B64D 27/404: {Suspension arrangements specially adapted for supporting vertical loads} - B64D 27/406: {Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links} - F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing - F02K 3/06: with front fan - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/90: Mounting on supporting structures or systems - F05D 2260/20: Heat transfer, e.g. cooling - Y02T 50/60: Efficient propulsion technologies, e.g. for 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) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A gas turbine engine comprises, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module. The gas turbine engine comprises first and second engine mount planes. The first and second engine mount planes are configured to support gas turbine engine in machine body. The gas turbine engine has axial length L, with axial length extending from inlet face of engine to exhaust face of engine. The first engine mount plane is positioned axially along gas turbine engine at first engine mount plane position, with first engine mount plane position within a range of between 0.24*L to 0.32*L from the inlet face of the engine. The second engine mount plane is positioned axially along gas turbine engine at second engine mount plane position, with second engine mount plane position within a range of between 0.73*L to 0.79*L from the inlet face of the engine. ## Claims ### Claim 1 A gas turbine engine, the gas turbine engine comprising, in axial flow sequence, a fan assembly, a compressor module, a turbine module, and an exhaust module, the gas turbine engine comprising a first engine mount plane and a second engine mount plane, each of the first engine mount plane and second engine mount plane being defined by a respective set of a first side engine mount point, a second side engine mount point, and a centre engine mount point, the first and second engine mount planes being configured to support the gas turbine engine in a machine body, the gas turbine engine having an axial length L, the axial length extending from an inlet face of the engine to an exhaust face of the engine, and wherein the first engine mount plane is positioned axially along the gas turbine engine at a first engine mount plane position, the first engine mount plane position being within a range of between 0.24*L to 0.32*L from the inlet face of the engine, and the second engine mount plane is positioned axially along the gas turbine engine at a second engine mount plane position, the second engine mount plane position being within a range of between 0.73*L to 0.79*L from the inlet face of the engine. ### Claim 2 (depends on 1) The gas turbine engine as claimed in claim 1, wherein the gas turbine engine comprises in axial flow sequence, a heat exchanger module, the fan assembly, the compressor module, the turbine module, and the exhaust module, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. ### Claim 3 (depends on 1) The gas turbine engine as claimed in claim 1, wherein the gas turbine engine is a turbofan gas turbine engine. ### Claim 4 (depends on 1) The gas turbine engine as claimed in claim 1, further comprising, at the first engine mount plane position, a mounting frame connected to both a first side and a second side of the engine, the mounting frame providing restraint to the engine in both the vertical direction and the lateral direction. ### Claim 5 (depends on 4) The gas turbine engine as claimed in claim 4, wherein at the second engine mount plane position, the first side engine mount point providing restraint to the engine in the vertical direction, the centre engine mount point providing restraint to the engine in both the lateral direction and the axial direction, and the second side engine mount point providing restraint to the engine in the vertical direction. ### Claim 6 (depends on 4) The gas turbine engine as claimed in claim 4, wherein at the second engine mount plane position, the first side engine mount point providing restraint to the engine in the vertical direction, and the second side engine mount point providing restraint to the engine in the vertical direction and in the lateral direction and in the axial direction. ### Claim 7 (depends on 4) The gas turbine engine as claimed in claim 4, wherein at the second engine mount plane position, the first side engine mount point providing restraint to the engine in both the vertical direction and the axial direction, and the second side engine mount point providing restraint to the engine in both the vertical direction and in the axial direction. ### Claim 8 (depends on 1) The gas turbine engine as claimed in claim 1, wherein at the first engine mount plane position, the second side engine mount point providing restraint to the engine in both the vertical direction and in the lateral direction. ### Claim 9 (depends on 1) The gas turbine engine as claimed in claim 1, wherein at the first engine mount plane position, the second side engine mount point providing restraint to the engine in the lateral direction, and the centre engine mount point providing restraint to the engine in the vertical direction. ### Claim 10 (depends on 1) The gas turbine engine as claimed in claim 1, wherein at the first engine mount plane position, the first side engine mount point providing restraint to the engine in the vertical direction, and the second side engine mount point providing restraint to the engine in the vertical direction. ### Claim 11 (depends on 10) The gas turbine engine as claimed in claim 10, wherein at the second engine mount plane position, the first side engine mount point providing restraint to the engine in the axial direction, and the second side engine mount point providing restraint to the engine in the vertical direction, in the lateral direction and in the axial direction. ### Claim 12 (depends on 10) The gas turbine engine as claimed in claim 10, wherein at the second engine mount plane position, the first side engine mount point providing restraint to the engine in the axial direction, the centre engine mount point providing restraint to the engine in the vertical direction, and the second side engine mount point providing restraint to the engine in both the lateral direction and in the axial direction. ### Claim 13 (depends on 1) The gas turbine engine as claimed in claim 1, wherein at the first engine mount plane position, the second side engine mount point providing restraint to the engine in the vertical direction. ### Claim 14 (depends on 13) The gas turbine engine as claimed in claim 13, wherein at the second engine mount plane position, the first side engine mount point providing restraint to the engine in both the vertical direction and the axial direction, and the second side engine mount point providing restraint to the engine in the vertical direction, in the lateral direction and in the axial direction. ### Claim 15 (depends on 1) The gas turbine engine as claimed in claim 1, wherein at the first engine mount plane position, the centre engine mount point providing restraint to the engine in the vertical direction. ### Claim 16 (depends on 1) The gas turbine engine as claimed in claim 1, wherein at the first engine mount plane position, the first side engine mount point providing restraint to the engine in the vertical direction, and the second side engine mount point providing restraint to the engine in both the vertical direction and the lateral direction. ### Claim 17 (depends on 16) The gas turbine engine as claimed in claim 16, wherein at the second engine mount plane position, the second side engine mount point providing restraint to the engine in the vertical direction, in the lateral direction and in the axial direction. ### Claim 18 (depends on 16) The gas turbine engine as claimed in claim 16, wherein at the second engine mount plane position, the centre engine mount point providing restraint to the engine in the vertical direction, and the second side engine mount point providing restraint to the engine in both the lateral direction and in the axial direction. ### Claim 19 (depends on 1) An aircraft comprising at least one gas turbine engine as claimed in claim 1.