IP Library Granted Patent US 8,956,487
Granted Patent B2
US 8,956,487 · App. 13/186,621 · Granted Feb 17, 2015

Rotor blade of a gas turbine engine made of composite material comprising a connecting yoke, method for manufacturing the blade

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Quick Facts
Patent No.
US 8,956,487
App. No.
13/186,621
Granted
Feb 17, 2015
Kind
B2
Abstract

A rotor blade of a turbine engine comprising a body made of composite material consisting of a fiber-reinforced thermosetting resin and a connecting yoke designed to be attached to a fastener of a rotor disc of the said turbine engine, the said blade characterized in that the connecting yoke comprises a metal reinforcement and a casing made of composite material encasing the said reinforcement.

Claims (11)

1. A method for manufacturing a rotor blade of a gas turbine engine including a body made of composite material and a connecting yoke designed to be attached to a fastener of a rotor disc of the turbine engine, the method comprising the following steps:

installing fibers around a metal tube;

injecting thermosetting resin in order to form a casing of composite material around the metal tube, the tube including

at least two sections having a first density of fibers, and

at least one section having a second density of fibers arranged between the two sections having a first density of fibers, the second density being less than the first density and greater than zero; and

machining the section having the second density of fibers so as to remove a portion of the metal tube around which is installed the second density of fibers, and to thereby form a connecting yoke for the blade including the two sections having the first density of fibers, forming a reinforcement of the connecting yoke, encased in composite material.

2. The method according to claim 1 , wherein the installing fibers includes weaving the fibers around the metal tube, the weave including warp threads placed along a cord of the blade and weft threads placed along a height of the blade.

3. The method according to claim 2 , wherein the weft threads are woven so as to surround a circumference of the metal tube.

4. The method according to claim 2 , wherein the weft threads and the warp threads are woven so as to surround a circumference of the metal tube.

5. The method according to claim 1 , wherein the installing fibers includes weaving fibers at right angles to one another.

6. The method according to claim 1 , wherein the installing fibers includes weaving fibers obliquely with one another.

Assignments (2)
CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Recorded Aug 24, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046939/0336 →
CHANGE OF NAME Recorded May 23, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046479/0807 →