Device to lock the blades of a turboblower and to fasten the front cowl of a turbojet engine
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorJean M. Surdi
Life of this patent
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Abstract
Device for the locking of blade roots and the fastening of the forward cowl consisting of a fastening piece comprising a parallelepipedic part (16) engaging radial slots (5) of the teeth (4) of the rim, a prismatic part (17), the convergent faces of which are resting against the sides of the groove and a cylindrical part (22) for the fastening of the cowl (24). The parallelepipedic (16) and prismatic (17) parts are parallel to each other and perpendicular to the cylindrical part (22). The cowl (24) has perforated counterbores (25) through which the cylindrical parts (22) are passing, with the ends of the cylindrical parts receiving a screw (27) to fasten the cowl.
Claims5
In a locking device for the blades of a fan and for fastening the forward cowl of a turbojet engine, the roots of said blades being maintained in axial grooves with a dovetail configuration on the rim of a rotor disk by means of wedges placed between the blade root and the bottom of the groove, with teeth formed in the axial upstream extension of the rim comprising opposed radial slots, the improvement comprising:
- a fastening piece (15) consisting of three parts:
- a first parallelepipedic part (16) engaging the radial slots (5) of the teeth (4) of the rims, a second prismatic part (17) the convergent faces (18, 19) whereof define an angle at the apex equal to that of the sides (20, 21) of the dovetail of the axial grooves (3) extending into the teeth and against which it radially abuts, and a third cylindrical part (22) threaded at least in part to receive fastening means (27) for the forward cowl (24), the first and the second parts (16, 17) being parallel to each other and perpendicular to the axis of the third part (22).
Dependencies are inferred from the claim text.