An unducted fan comprises a hub (28 fig 2) and blades 36. The hub (28 fig 2) comprises cowls 46 fixed to upstream 38 and downstream 39 collars. The cowl 46 comprises a joint edge 48c which is contiguous with a complementary joint edge 48d of an adjacent cowl 46. The cowls 46 can be removed by a movement including pivoting about an initial pivot axis C and during the pivoting the joint edge 48c moves away from the complementary joint edge 48d by moving towards the inside of the hub (28 fig 2). The initial pivot axis C may pass through a pivot region of contact between the cowl 46 and the upstream 38 and/or downstream 39 collar. Each cowl 46 may have a first 50a, 51a and second 50b, 51b joint edges connected by a concave curved edge 52a. The joint edges 48c, 48d may have a bevelled end potion 54. Each cowl 46 may comprise a lug (59 fig 11) of reduced thickness which can be covered by a complementary lug (58 fig 11) of the adjacent cowl 46. This arrangement allows the cowls 46 to be removed for maintenance.
Unducted fan for an aircraft turbine engine
2016-09-28
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE
European Patent Office | 2023
|AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE
European Patent Office | 2023
|