Air intake module for an aircraft turbomachine and method for de-icing thereof
AssigneeSafran Nacelles
InventorPierre Charles Caruel
Life of this patent
Estimating the term…
Abstract
An air intake module for an aircraft turbomachine extending along a longitudinal axis oriented from upstream to downstream and including an inner wall and an outer wall defining together a vein for circulating an air flow, a plurality of guide vanes of the air flow extending radially in the vein and each comprising an upstream leading edge, at least one stator member fixedly mounted on the inner wall and on the outer wall and extending radially in the vein upstream of the guide vanes, the stator member comprising an infrared wave emitting device configured to emit an infrared beam on the leading edge of at least one of the guide vanes for de-icing it.
Claims15
An air intake module for an aircraft turbomachine, said air intake module extending along a longitudinal axis oriented from upstream to downstream and being configured to be mounted downstream of a propeller of the aircraft turbomachine, said air intake module comprising:
- an inner wall and an outer wall, the outer wall extending around the inner wall, the inner wall and the outer wall cooperating to define a vein for circulating an air flow,
- a plurality of guide vanes of the air flow extending radially in the vein and each comprising an upstream leading edge,
- at least one stator member fixedly mounted on the inner wall and on the outer wall and extending radially in the vein upstream of the guide vanes,
- wherein said at least one stator member comprises an infrared wave emitting device integrated therein, the infrared wave emitting device extending radially in the vein upstream of the guide vanes so as to emit an infrared beam on the leading edge of at least one of the guide vanes.
A method for de-icing an air intake module of an aircraft turbomachine, the method comprising the steps of:
- providing the air intake module extending along a longitudinal axis oriented from upstream to downstream and being configured to be mounted downstream of a propeller of the aircraft turbomachine, the air intake module including an inner wall and an outer wall, the outer wall extending around the inner wall, the inner wall and the outer wall cooperating to define a vein for circulating an air flow, a plurality of guide vanes of the air flow extending radially in the vein and each comprising an upstream leading edge, at least one stator member fixedly mounted on the inner wall and on the outer wall and extending radially in the vein upstream of the guide vanes, said at least one stator member including an infrared wave emitting device integrated therein, the infrared wave emitting device extending radially in the vein upstream of the guide vanes;
- and
- emitting an infrared beam with the infrared wave emitting device onto the leading edge of at least one of the guide vanes.
Dependencies are inferred from the claim text.