Gas turbine engine e.g. turboshaft engine, for use in nacelle of aircraft, has exchanger fixed on intermediate wall connecting annular aerodynamic walls and longitudinal reinforcement connecting leading edge of lip with intermediate wall

摘要

The engine (1) has air-oil heat exchangers (14A-14C) arranged inside an air intake sleeve (12) for cooling oil. The air intake sleeve is hollow in shape and defines an interior volume. Each exchanger is arranged inside the interior volume. The sleeve has shape of an annular lip formed by two external (12Ex) and internal (12In) annular aerodynamic walls connected to a level of a leading edge (12B). The exchanger is fixed on an intermediate wall (15) connecting the annular aerodynamic walls. A longitudinal reinforcement connects the leading edge of the lip with the intermediate wall.