SYSTÈME DE GESTION THERMIQUE DE MOTEUR À PROPULSION

摘要

A propulsion engine (102) for an aeronautical vehicle defines a radial direction (R) and a cooling air flowpath (132). The propulsion engine (102) includes a power source (104); and a fan (112) including a fan blade (122) rotatable by the power source (104) and extending generally along the radial direction (R), the fan blade (122) defining an inlet (134), an outlet (136), and a cooling air passage (138) extending between the inlet (134) and the outlet (136) and in airflow communication with the cooling air flowpath (132), the inlet (134) being positioned inward from the outlet (136) along the radial direction (R) to provide a cooling airflow (146) through the cooling air flowpath (132).