IP Library Granted Patent US 7,556,083
Granted Patent B2
US 7,556,083 · App. 11/687,740 · Granted Jul 7, 2009

Process for manufacturing the blade of a turbomachine, and assembly of the cores for implementation of the process

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Quick Facts
Patent No.
US 7,556,083
App. No.
11/687,740
Granted
Jul 7, 2009
Kind
B2
Abstract

A plugged assembly of cores includes a first core having a first end portion, and a second core having a second end portion. The first end portion of the first core is connected to the second end portion of the second core by a mortise and tenon type connection to form an assembly of the two cores having residual spaces formed by the mortise and tenon type connection, such residual spaces being liable to give rise to flashings when metal is poured over the assembly if not plugged. Residual spaces formed by the mortise and tenon type connection in the assembly of the two cores contain a material configured to reduce the possibility of flashings.

Claims (17)

1. A plugged assembly of cores for forming a blade including a central longitudinal cavity and a plurality of outer longitudinal cavities positioned adjacent to the central longitudinal cavity, comprising:

a first core of a ceramic material having a body configured to form the central longitudinal cavity and having a first end portion including a mortise; and

a second core of said ceramic material having a body configured to form the plurality of outer longitudinal cavities and having a second end portion including a tenon to form a mortise and tenon type connection with the first core, wherein

the first end portion of the first core is connected to the second end portion of the second core by the mortise and tenon type connection to form residual spaces joining a first end of the central longitudinal cavity and first ends of the plurality of outer longitudinal cavities,

wherein the first core and the second core are only connected at the mortise and tenon type connection such that the central longitudinal cavity and the plurality of outer longitudinal cavities are only directly connected at the residual spaces,

said residual spaces formed by the mortise and tenon type connection in the assembly of the two cores contain a material other than said ceramic material and are configured to reduce the possibility of flashings, and

said material is positioned within said residual spaces such that said residual spaces are free of metal after said metal is poured over said assembly.

2. A plugged assembly according to claim 1 , wherein the material contained in the residual spaces formed by the mortise and tenon type connection is ceramic mastic.

3. A plugged assembly according to claim 1 , further comprising a third core connected to the first core.

4. A plugged assembly according to claim 3 , wherein at least one of the second and third cores includes at least two parallel branches.

5. A plugged assembly according to claim 3 , wherein

the third core includes a third end portion formed with a second tenon corresponding to a second mortise formed on the first core, and

the second tenon formed on the third end portion is formed at a top of the third core.

6. A plugged assembly according to claim 1 , wherein the tenon formed on the second end portion is formed at a top of the second core.

7. A plugged assembly according to claim 1 , wherein

the plurality of outer longitudinal cavities in the second core includes three longitudinal cavities.

8. A plugged assembly according to claim 7 , wherein the body of the second core includes three parts configured to form the three longitudinal cavities and the three parts are separated by gaps such that the gaps do not include any pieces in the gaps to connect the three parts.

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 →