# US 2023/0058042 A1 · Filling an aircraft turbine engine lubricant tank > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2023/0058042 A1 - Document ID: US20230058042A1 - Status: Published application - Kind: A1 - Application number: 17/904,312 - Filed: 2021-02-15 - Published: 2023-02-23 - Earliest claimed: 2020-02-21 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Claire Alexia BERGO - Web page: https://patentgrep.com/patent/US20230058042A1 ## CPC - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F01D 25/18: Lubricating arrangements (of machines or engines in general F01M) - F01M 11/0458: {Lubricant filling and draining} - F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) - F02K 3/04: the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type - F05D 2230/72: Maintenance - F05D 2260/98: Lubrication - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F01M: LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A dual flow turbine engine includes at least one lubricant tank located in an annular space of the turbine engine body and at least one hatch which is provided on an external cowling of a nacelle, for filling the tank. The tank is configured to be filled, by means of a removable tubular pipe inserted from the hatch into the tank, through canisters. One of the canisters includes a first interface through which the pipe is configured to pass, and another canister includes a second interface for connecting the pipe to the tank. ## Claims ### Claim 1 A dual flow turbine engine, comprising: a gas generator, a nacelle which surrounds the gas generator, arms configured to connect the gas generator to the nacelle, an annular duct for the flow of a primary flow, the duct being formed in the gas generator and being externally delimited by a first annular casing of the gas generator, an annular duct for the flow of a secondary flow, the duct being formed between the gas generator and the nacelle and being delimited internally by a second annular casing of the gas generator and externally by a third annular casing surrounded by the nacelle, the second and third casings being connected together by at least some of said arms, at least one lubricant tank located in an annular space extending between the first and second casings, at least one hatch provided on an outer cowling of the nacelle, for filling said tank, wherein said tank is configured to be filled by means of a removable tubular pipe inserted from said hatch to the tank, said third casing comprising a first interface configured to be passed through by said pipe, and said second casing comprising a second interface configured to connect the pipe to said tank. ### Claim 2 (depends on 1) The turbine engine according to claim 1, wherein said first and second interfaces are located directly in said duct for the flow of the secondary flow. ### Claim 3 (depends on 2) The turbine engine according to claim 2, wherein said first interface comprises a telescopic guiding system comprising a plurality of elements mounted coaxially and slidably one inside the other, the system being configured to be passed through by the pipe and to adopt a first retracted position in which the system has a minimum length or thickness and does not project into the duct for the flow of the secondary flow, and a second extended position in which the system has a maximum length or thickness and projects into the duct for the flow of the secondary flow towards the second interface. ### Claim 4 (depends on 1) The turbine engine according claim 1, wherein said second interface comprises a connection device comprising: an end-piece configured to cooperate by male-female nesting with a complementary end-piece on a distal end of the pipe, and a mechanism configured to open the tank when the nesting is effective. ### Claim 5 (depends on 4) The turbine engine according to claim 4, wherein said opening mechanism comprises at least one portion movable from a closed position to an open position of the tank, the movable portion being biased by an elastic member into its closed position and being brought to its open position by said male-female nesting. ### Claim 6 (depends on 4) The turbine engine according to claim 4, wherein said second interface comprises a guiding and locking element configured to cooperate by bayonet effect with an element complementary to the end-piece on the pipe. ### Claim 7 (depends on 1) The turbine engine according to claim 1, wherein the hatch is located upstream of thrust reverser covers of the turbine engine. ### Claim 8 (depends on 1) An assembly comprising a turbine engine according to claim 1 and a removable tubular pipe configured to fill the tank, to pass through said first interface, and to be connected to the tank via said second interface. ### Claim 9 (depends on 8) The assembly according to claim 8, wherein the pipe comprises a distal end equipped with an end-piece configured to cooperate by male-female nesting with a complementary end-piece of the second interface, this end-piece being equipped with a shutter device arranged to open the distal end of the pipe when this nesting is effective and to close said distal end when said end-piece and said complementary end-piece are disengaged from each other. ### Claim 10 (depends on 3) An assembly comprising the turbine engine according to claim 3 and a removable tubular pipe configured to fill the tank, to pass through said first, and to be connected to the tank via said second interface, wherein the pipe comprises at least one member movable between a retracted position along the pipe, and an extended position projecting from the pipe, this movable member being configured to cooperate with said system in order to force the system to retract when the pipe is removed from the turbine engine. ### Claim 11 (depends on 1) The assembly comprising the turbine engine of claim 1 and a removable tubular pipe configured to fill the tank, to pass through said first interface, and to be connected to the tank via said second interface, wherein said first interface is formed by an opening provided in said third casing, said hatch comprises a movable member for closing the hatch equipped with a shutter arranged to close said opening when the hatch is closed, and the pipe is associated with a guiding system arranged to be installed at the location of the hatch once the latter is open and to be uninstalled once the tank is filled. ### Claim 12 (depends on 8) A method for filling a lubricant tank n an aircraft turbine engine, by means of an assembly according claim 8, comprising the steps of: opening the hatch of the nacelle, inserting the pipe through the hatch and then through the first interface, passing the pipe through the duct for the flow of the secondary flow to the second interface for connecting the pipe to the tank, and flowing lubricant from a proximal end of the pipe located outside the turbine engine to a distal end of the pipe and to the tank.