# US 11,078,848 B2 · Gas turbine engine fireproofing > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,078,848 B2 - Document ID: US11078848B2 - Status: Granted - Kind: B2 - Application number: 16/142,109 - Filed: 2018-09-26 - Published: 2019-04-11 - Granted: 2021-08-03 - Earliest claimed: 2017-10-09 - Assignees: ROLLS-ROYCE plc - Applicants: ROLLS-ROYCE plc - Inventors: Richard Peace - Web page: https://patentgrep.com/patent/US11078848B2 ## CPC - F02C 7/25: Fire protection or prevention (in general A62) - A62C 2/06: Physical fire-barriers - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - B64D 2045/009: {Fire detection or protection; Erosion protection, e.g. from airborne particles} - F02K 3/06: with front fan - F05D 2240/15: Heat shield - F05D 2260/231: Preventing heat transfer - 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) - A62C: FIRE-FIGHTING (fire-extinguishing compositions, use of chemical substances in extinguishing fires A62D1/00; spraying, applying liquids or other fluent materials to surfaces in general B05; alarm arrangements G08B, e.g. fire alarms actuated by smoke or gases G08B17/10) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - 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 has a nacelle providing an external skin of the engine, a casing structure radially inwards of the external skin and providing an outer surface of an air flow duct of the engine, and plural engine components located in the bay formed between the casing structure and the nacelle. The components are part of either a first set of components or a second set of components. The components of the first set are all the components from the bay which are potential ignition sources, and the components of the second set are all the remaining components from the bay. The engine further has a container located in the bay, the container being fireproof capable of withstanding the application of heat by a standard flame for 15 minutes and the container containing the components of the first set. ## Claims ### Claim 1 A gas turbine engine comprising: a nacelle; a casing structure radially inwards of the nacelle and providing an outer surface of an air flow duct of the engine, plural engine components located in a bay formed between the nacelle and the casing structure, the plural engine components being part of either a first set of components or a second set of components, wherein the first set of components are all components of the plural engine components which are potential ignition sources, and the second set of components are all remaining components of the plural engine components; and a container located in the bay, the container being fireproof such that the container is capable of withstanding an application of heat by a standard flame for 15 minutes, wherein the first set of components includes at least an accessory gearbox and the second set of components includes at least one or more engine electronic controllers and one or more electrical harnesses, wherein, with an exception of the one or more electrical harnesses, the container contains only the first set of components, and wherein the container envelopes the accessory gearbox. ### Claim 2 (depends on 1) The gas turbine engine according to claim 1, wherein the container is a single fireproof container located in the bay. ### Claim 3 (depends on 1) The gas turbine engine according to claim 1, wherein the first set of components includes the accessory gearbox and fuel lines which extend from the accessory gearbox. ### Claim 4 (depends on 3) The gas turbine engine according to claim 3, wherein the first set of components further includes hydraulic lines which extend from the accessory gearbox. ### Claim 5 (depends on 1) The gas turbine engine according to claim 1, wherein the second set of components includes the one or more engine electronic controllers, one or more oil tanks, oil lines which extend from the oil tanks, an aircraft air system, engine mounts for mounting the engine to an airframe, one or more air/oil heat exchangers, and the one or more electrical harnesses. ### Claim 6 (depends on 5) The gas turbine engine according to claim 5, wherein the engine mounts are formed of aluminium alloy or composite material. ### Claim 7 (depends on 5) The gas turbine engine according to claim 5, wherein the second set of components further includes one or more engine health monitoring units. ### Claim 8 (depends on 1) The gas turbine engine according to claim 1, wherein the accessory gearbox is aligned in an axial direction of the engine. ### Claim 9 (depends on 1) The gas turbine engine according to claim 1, wherein the container is at least partly recessed into the casing structure. ### Claim 10 (depends on 1) The gas turbine engine according to claim 1 which is a ducted fan engine, wherein the air flow duct is a bypass duct that surrounds a core engine.