Jet engine device with a bypass flow channel

The device (1) has a set of strut-like support elements (17) connected at one end to an inner wall (3) and at another end to an outer wall (4). Each support element has a thickness distribution defined along a central longitudinal plane (21). Each plane forms a positive acute angle (17G) with an engine axis (6) in an area (B) of the support element adjacent the inner wall, and a negative acute angle (17H) with the engine axis in an area (A) of the support element adjacent the outer wall to enlarge flow cross-sections in acute angle areas (17A, 17B) adjacent the inner and outer walls.