An assembly for a gas turbine engine comprising: - a nacelle having a longitudinal axis (X-X) and comprising an intake lip defining an air intake , and - a device for modifying the geometry of the air intake , said device comprising: - a first slat , and - a second slat , the first slat and the second slat being mobile in translation according to the longitudinal axis (X-X) relative to the nacelle between: - a first configuration where the first slat forms the intake lip and the second slat extends inside the nacelle , and - a second configuration where the first slat extends at a distance from the intake lip , and the second slat forms the intake lip so as to define an airflow channel between a downstream surface of the first slat and an upstream surface of the second slat , The assembly being characterized in that the first slat has: - in a first radial plane (P1) relative to the longitudinal axis (X-X), a first downstream profile of the first slat (C21), and - in a second radial plane (P2) relative to the longitudinal axis (X-X), a second downstream profile of the first slat (C22), the second downstream profile of the first slat (C22) being different to the first downstream profile of the first slat (C21), such that the airflow channel has, in the first radial plane (P1), a first longitudinal section, and in the second radial plane (P2), a second longitudinal section, the second longitudinal section being different to the first longitudinal section. - a nacelle having a longitudinal axis (X-X) and comprising an intake lip defining an air intake , and - a device for modifying the geometry of the air intake , said device comprising: - a first slat , and - a second slat , - a first slat , and - a second slat , the first slat and the second slat being mobile in translation according to the longitudinal axis (X-X) relative to the nacelle between: - a first configuration where the first slat forms the intake lip and the second slat extends inside the nacelle , and - a second configuration where the first slat extends at a distance from the intake lip , and the second slat forms the intake lip so as to define an airflow channel between a downstream surface of the first slat and an upstream surface of the second slat , - a first configuration where the first slat forms the intake lip and the second slat extends inside the nacelle , and - a second configuration where the first slat extends at a distance from the intake lip , and the second slat forms the intake lip so as to define an airflow channel between a downstream surface of the first slat and an upstream surface of the second slat , The assembly being characterized in that the first slat has: - in a first radial plane (P1) relative to the longitudinal axis (X-X), a first downstream profile of the first slat (C21), and - in a second radial plane (P2) relative to the longitudinal axis (X-X), a second downstream profile of the first slat (C22), - in a first radial plane (P1) relative to the longitudinal axis (X-X), a first downstream profile of the first slat (C21), and - in a second radial plane (P2) relative to the longitudinal axis (X-X), a second downstream profile of the first slat (C22), the second downstream profile of the first slat (C22) being different to the first downstream profile of the first slat (C21), such that the airflow channel has, in the first radial plane (P1), a first longitudinal section, and in the second radial plane (P2), a second longitudinal section, the second longitudinal section being different to the first longitudinal section. <EOS>