BLADE-RETAINING DEVICE FOR TURBOMACHINE PROPELLER
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Abstract
An aircraft turbomachine propeller including multiple blades assembled on a hub rotating around an axis of rotation of the propeller, that can reduce risks of loss of the blade following impact of a foreign body. At least one blade includes a recess opening radially towards the inside in the area of the base of this blade. A retaining device includes a moving retaining mechanism positioned in the recess and configured to be moved from a retracted position to a deployed blade-retaining position, and vice versa.
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Citations
20 Claims
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1-10. -10. (canceled)
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11. An aircraft turbomachine propeller, comprising:
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multiple blades, each including a base assembled on a hub rotating around an axis of rotation of the propeller, wherein at least one blade includes a recess opening radially towards the inside in an area of a base of this blade, and wherein the propeller includes, in association with the recess, a blade-retaining device that is stationary in terms of translational motion in a radial direction towards the outside relative to the hub, including moving retaining means positioned in the recess and configured to occupy; a retracted position in which the moving retaining means does not form a stop for the blade in the radial direction towards the outside; a deployed position in which the moving retaining means forms a stop for the blade in the radial direction towards the outside; and to be moved from one to the other of the positions. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20)
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Specification