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US 2023/0058042 A1Published application
Filling an aircraft turbine engine lubricant tank
AssigneeSafran Aircraft Engines
InventorClaire Alexia BERGO
Life of this patent
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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.
Claims12
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.
5 more elements
Dependencies are inferred from the claim text.