Air inlet of a turbomachine nacelle including a circulation conduit of a hot air flow between a movable upstream part and a fixed downstream part

An air inlet of a nacelle for an aircraft turbomachine extending along an axis in which an air flow circulates from upstream to downstream, the air inlet extending annularly about the axis, the air inlet comprising:

• a movable upstream part and a fixed downstream part,
• at least one controllable moving member configured to move, during operation of the turbomachine, the movable upstream part between a retracted position in which the movable upstream part is adjacent to the fixed downstream part and an extended position in which the movable upstream part is movable away from the fixed downstream part to allow circulation of a through air flow to flow between the movable upstream part and the fixed downstream part,
• at least one de-icing circuit comprising at least one circulation conduit fluidly connecting the movable upstream part and a hot air source, the at least one de-icing circuit is configured to circulate hot air in the at least one circulation conduit so as to inject hot air flow into the movable upstream part, wherein the at least one circulation conduit comprises:
• at least one upstream non-telescopic piping slidably mounted at an upstream end of the fixed downstream part, and
• at least one downstream telescopic member comprising at least one internal piping mounted in an external piping and the internal and external pipings in fluid connection with one another, the at least one internal piping being fluidly connected to the at least one upstream non-telescopic piping, the external piping being fluidly connected to the hot air source, and the at least one internal piping being configured to move only in the fixed downstream part.

An air inlet of a nacelle for an aircraft turbomachine extending along an axis in which an air flow circulates from upstream to downstream, the air inlet extending annularly about the axis, the air inlet comprising:

• an upstream part and a downstream part, wherein the downstream part is fixed relative to a reference point and the upstream part is movable relative to the downstream part;
• a controllable moving member configured to move, during operation of the turbomachine, the upstream part between a retracted position in which the upstream part is located adjacent to the downstream part and an extended position in which the upstream part is movable away from the downstream part and a gap is located between the upstream part and the downstream part for air flow to flow into the gap between the upstream part and the downstream part,
• a de-icing circuit comprising a circulation conduit fluidly connecting the upstream part to a hot air source, the de-icing circuit is configured to circulate hot air in the circulation conduit and the upstream part, wherein the circulation conduit comprises:
• an upstream non-telescopic piping slidably mounted at an upstream end of the downstream part, and
• a downstream telescopic member comprising an internal piping mounted in an external piping and the internal and external pipings in fluid connection with one another, the at least one internal piping being fluidly connected to the upstream non-telescopic piping, the external piping being fluidly connected to the hot air source, and the internal piping being configured to move in the downstream part.