A flexible mounting for a star‐type aircraft engine comprises an annular support and a radial flange on the engine having parts which spigotally engage one another through resilient means, attachment bolts carried by the support, or by the flange, and extending through the other with clearance, and resilient means located on the support and on the flange to absorb the engine torque reaction chiefly in shear. As shown in Fig. 1, a flange 11 of an aircraft engine is secured to an annular box section 14, 15, 16 on the aircraft by bolts 18 and resilient pads of rubber, &c, 24, 28. A collar 22 on each bolt secures to the flange 11 an L‐shaped flange 20 and a plate 23 to which the pad 24 is vulcanised, an extension 27 of the pad forming a resilient spigot, adjoining backing plates 26, 29, may overlap and are secured to the box‐section by bolts. In Fig. 6, the side 15b of the box‐section is extended to form a spigot 20a and the bolt 18a is rigidly connected through distance pieces 40, 37 with the box section. The flange 11a of the engine floats between the pad pieces 28a, 24a and bears on the extension 27a of the pad piece 24a. The pads 24 may comprise an annular ring and the pads 28 may be replaced by radial rollers.
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