AIR INTAKE LIP OF AN AIRCRAFT ENGINE NACELLE, COMPRISING AT LEAST ONE INFRARED EMISSION SOURCE

The invention relates to an air intake lip of an aircraft engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the lip extending annularly about the X-axis and having an inner wall facing the X-axis and an outer wall which is opposite the inner wall,...

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Bibliographic Details
Main Authors Gonidec, Patrick, Rami, Jean-Paul
Format Patent
LanguageEnglish
Published 14.07.2022
Subjects
AEROPLANES
AIR INTAKES FOR JET-PROPULSION PLANTS
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
COSMONAUTICS
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
GAS-TURBINE PLANTS
HEATING
HELICOPTERS
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
PARACHUTES
PERFORMING OPERATIONS
TRANSPORTING
WEAPONS
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Summary:The invention relates to an air intake lip of an aircraft engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the lip extending annularly about the X-axis and having an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the inner wall and the outer wall being connected by an upstream wall and a partition so as to delimit an annular cavity, in which at least one infrared emission source is housed, wherein at least one wall, selected among the inner wall, the outer wall and the upstream wall, is made of a material configured to transmit on an outer face at least 30% of the infrared received on an inner face.
Bibliography:Application Number: US202017614146