Embodiments of the present invention provide an inlet particle separator (100) for a gas turbine engine having an inlet flow path (102), a scavenge flow path (104), a core flow path (106), and a flow splitter (114) disposed between the scavenge and core flow paths. A plurality of grooves (200) may be disposed about an inner surface of a wall of the separator within the inlet flow path (102).
Gas turbine engine particle separator
Partikelabscheider für einen Gasturbinenmotor
Séparateur de particules de moteur à turbine à gaz
2017-06-28
Patent
Electronic Resource
English