IP Library › Granted Patent US 10,471,556
Granted Patent B2
US 10,471,556 · App. 15/759,169 · Granted Nov 12, 2019

Method for producing a protective reinforcement for a blade (P) having a curved leading edge or trailing edge

Inventors: Remi Philippe Guy Onfray (Moissy-Cramayel, FR); Maxime Briend (Moissy-Cramayel, FR); Didier Pelletier (Moissy-Cramayel, FR)
Assignee: SAFRAN AIRCRAFT ENGINES
B23P15/04B21D53/78B23H5/04B23K26/0093F01D5/147F01D5/28F04D29/289F04D29/324B23K2101/001F05D2220/32F05D2230/20F05D2240/303
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Quick Facts
Patent No.
US 10,471,556
App. No.
15/759,169
Granted
Nov 12, 2019
Kind
B2
Abstract

The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening ( 102 ) a hollow tube ( 1 ) so as to form at least one fold line ( 6 ) extending along the tube ( 1 ), opening ( 104 ) the flattened tube ( 1 ) by cutting the tube ( 1 ) along a cutting line ( 8 ) opposite the fold line ( 6 ) with respect to the tube ( 1 ), so as to form two flanks ( 16, 18 ) linked at the fold line ( 6 ) and intended to be mounted on the pressure side and the suction side of the blade (P), the method being characterised by a preliminary step ( 100 ) of bending the hollow tube ( 1 ) carried out before the flattening ( 102 ) and adapted such that the fold line ( 6 ) after flattening ( 102 ) is curved and substantially matches the curved leading edge (BA) of the blade (P).

Claims (18)

1. A method for manufacturing a protective reinforcement of a leading (BA) or trailing edge of a blade (P), wherein the leading (BA) or trailing edge is curved, wherein the method comprises:

flattening ( 102 ) a hollow tube ( 1 ) so as to form at least one fold line ( 6 ) extending along the tube ( 1 ),

opening ( 104 ) the flattened tube ( 1 ) by cutting the flattened tube ( 1 ) along a cut line ( 8 ) opposite to the fold line ( 6 ) with respect to the flattened tube ( 1 ), so as to form two flanks ( 16 , 18 ) connected to the fold line ( 6 ) and designed to be applied to the pressure side and the suction side of the blade (P),

wherein the method further comprises:

before flattening the hollow tube, bending ( 100 ) the hollow tube ( 1 ) so that the fold line ( 6 ) after flattening ( 102 ) is curved and substantially complementary to the curved leading (BA) or trailing edge of the blade (P).

2. The method according to claim 1 , wherein the bending ( 100 ) is cold bending.

3. The method according to claim 1 , wherein the flattening ( 102 ) of the hollow tube ( 1 ) forms on the tube ( 1 ) two opposite fold lines ( 6 , 8 ), and wherein the cut line ( 8 ) is one of the two fold lines.

4. The method according to claim 1 , wherein the tube ( 1 ) is made of metal.

5. The method according to claim 1 , further comprising stamping ( 106 ) the open tube ( 1 ) so as to comply the flanks ( 16 , 18 ) in a manner complementary to the pressure side and the suction side of the blade (P).

6. The method according to claim 5 , wherein the open tube ( 1 ) is stamped by means of a stamp (EM) into a groove (G) formed in a die (EF), wherein the groove (G) has a depth adapted so that at least one of the flanks of the tube ( 16 , 18 ) has a free end portion ( 20 , 22 ) projecting out of the groove (G) when the fold line is in abutment against the bottom of the groove (G), wherein the method further comprises cutting the free end portion ( 20 , 22 ).

7. The method according to claim 6 , wherein the cutting is a laser cutting.

8. The method according to claim 6 , wherein the cutting comprises wire EDM.

9. The method according to claim 5 , wherein the open tube ( 1 ) is stamped by means of a stamp into a groove formed in a die, wherein the groove has two opposite lateral openings and a length measured between the two lateral openings less than the length of the fold line of the open tube ( 1 ), wherein the open tube ( 1 ) is positioned in the groove (G) so that two free longitudinal end portions ( 24 , 26 ) thereof project out of the two lateral openings ( 0 ) of the groove (G), wherein the method further comprises cutting at least one of said free longitudinal end portions ( 24 , 26 ).

10. The method according to claim 9 , wherein the cutting is a laser cutting.

11. The method according to claim 9 , wherein the cutting comprises wire EDM.

12. A method for manufacturing a reinforced blade comprising:

manufacturing a protective reinforcement by means of a method according to claim 1 ,

attaching the protective reinforcement to a blade (P) comprising a curved leading (BA) or trailing edge, wherein the fold line ( 6 ) of the reinforcement is applied against the leading (BA) or trailing edge of the blade (P) and wherein the flanks ( 16 , 18 ) are applied to the pressure side and the suction side of the blade (P).

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Aug 13, 2018
From: ONFRAY, REMI PHILIPPE GUY; BRIEND, MAXIME; PELLETIER, DIDIER
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046784/0760 →
Priority Claims (1)
FR 15 58442 · Sep 10, 2015 · national
Continuity (1)
Related Publication 20180257185A1 · Sep 13, 2018
Cited By (3)
US 12,410,716 US 12,435,636 US 12,723,513