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AssigneeSafran
InventorsStéphan ZURBACH, Romain LE DORTZ
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A device for injecting a combustible mixture into a combustion chamber of a turbine of an aircraft turbine engine which has, about a longitudinal axis, a tubular central channel, a first annular channel about the central channel, and a second annular channel about the first annular channel, the channels being open to the combustion chamber at a first lip of the central channel, at a second lip of the first annular channel, and at an end of the second annular channel. The first annular channel includes, upstream of the second lip, a device for injecting dihydrogen into the first annular channel in an air flow passing along the longitudinal axis of the first annular channel so as to create a dihydrogen-air mixture flowing towards the combustion chamber.
An injection device for injecting a combustible air-dihydrogen mixture, for a combustion chamber (100) of a turbine of an aircraft turbine engine, characterized in that it comprises, about a longitudinal axis (X), a tubular central channel (1), a first annular channel (2) about the central channel, and a second annular channel (3) about the first annular channel (2), the channels (1, 2, 3) being configured so as to be open to the combustion chamber at a first lip (9) of the central channel, at a second lip (10) of the first annular channel, and at an end (11) of the second annular channel, the first annular channel comprising, upstream of the second lip (10), means for injecting dihydrogen (5, 6, 7) into the first annular channel (2) in an air flow (8) moving along the longitudinal axis of the first annular channel so as to produce a dihydrogen-air mixture flowing between the first lip and the second lip.
Dependencies are inferred from the claim text.