Jet pump for turbomachine lubrication chamber depressurization circuit

A turbomachine lubrication chamber depressurization device comprising a depressurization duct connecting an inner volume of a lubrication chamber to a secondary flow path of a turbomachine, in which flows a gas flow from the lubrication chamber to the secondary flow path of the turbomachine,

• the depressurization duct comprising a jet pump, for injecting an air flow into the gas flow, said air flow originating from a turbomachine compressor, the jet pump comprising:
• a tubular body in which flows the gas flow,
• a first injection duct for injection of a first air flow in the gas flow, which opens into the tubular body via a first tubular outlet nozzle located inside the tubular body and that is coaxial with a main axis of the tubular body and open at its downstream end,
• a second injection duct for injection of a second air flow in the gas flow, which opens into the tubular body via a second outlet nozzle located inside the tubular body that is coaxial with the main axis of the tubular body and that surrounds the first tubular outlet nozzle, the downstream end of the second outlet nozzle axially aligning with the downstream end of the first tubular outlet nozzle,
• wherein an upstream end of the first tubular outlet nozzle comprises an axial orifice centered on the main axis of the tubular body,
• and in that the jet pump comprises a plugging means for either plugging or not plugging said axial orifice of the first tubular outlet nozzle, wherein said plugging means physically contacts the axial orifice during a plugging operation.

An aircraft turbomachine comprising at least one bearing lubrication chamber and one lubrication chamber depressurization device, the one lubrication chamber depressurization device comprising a depressurization duct connecting an inner volume of the at least one bearing lubrication chamber to a secondary flow path of the aircraft turbomachine, in which flows a gas flow from the at least one bearing lubrication chamber to the secondary flow path of the aircraft turbomachine and a jet pump for the one lubrication chamber depressurization device, the jet pump comprising:

• a tubular body in which flows the gas flow,
• a first injection duct for injection of a first air flow in the gas flow, which opens into the tubular body via a first tubular outlet nozzle located inside the tubular body and that is coaxial with a main axis of the tubular body and open at its downstream end,
• a second injection duct for injection of a second air flow in the gas flow, which opens into the tubular body via a second outlet nozzle located inside the tubular body that is coaxial with the main axis of the tubular body and that surrounds the first tubular outlet nozzle, the downstream end of the second outlet nozzle being axially aligned with the downstream end of the first tubular outlet nozzle,
• wherein an upstream end of the first tubular outlet nozzle comprises an axial orifice centered on the main axis of the tubular body,
• and in that the jet pump comprises a plugging means for either plugging or not plugging said axial orifice of the first tubular outlet nozzle, wherein said plugging means physically contacts the axial orifice during a plugging operation.