Turbine engine blade preform

Patent metadata

Field	Value
Publication number	US-2016129497-A1
Application number	US-201414895777-A
Country	US
Kind code	A1
Filing date	Jun 4, 2014
Priority date	Jun 5, 2013
Publication date	May 12, 2016
Grant date	—

Abstract

The invention relates to a blade preform ( 46 ) including a strut connecting a plat-form ( 16 ) to a blade root portion ( 14 ) extending longitudinally in an upstream-downstream direction, an upstream web ( 26 ) and a downstream ( 28 ) web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream ( 26 ) and downstream ( 28 ) webs connect the upstream and downstream ends of the plat-form ( 16 ) to the upstream and downstream ends of the blade root ( 14 ). According to the invention, the blade root ( 14 ) extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs ( 26, 28 ) and the side edges ( 40 ) of each web ( 26, 28 ) are extended by walls that converge ( 44 ) at the flanks of the blade root.

First claim

1 . A turbine engine blade preform ( 46 ), with the preform comprising a strut connecting a plat-form ( 16 ) to a blade root portion ( 14 ) extending longitudinally in an upstream-downstream direction, an upstream web ( 26 ) and a downstream ( 28 ) web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut, with such upstream ( 26 ) and downstream ( 28 ) webs connecting the upstream and downstream ends of the plat-form ( 16 ) to the upstream and downstream ends of the blade root ( 14 ), characterized in that the blade root ( 14 ) extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that over which the upstream and downstream webs ( 26 , 28 ) extend in said direction and in that the upstream and downstream webs each comprise two side edges ( 40 ) which are extended by walls that converge ( 44 ) at the flanks of the blade root.

2 . A preform according to claim 1 , characterized in that said converging walls ( 44 ) are formed by plane faces inclined with respect to a median plane of the blade root extending longitudinally along an upstream/downstream direction.

3 . A preform according to claim 2 , characterized in that the faces ( 44 ) are inclined at an angle of approximately 45° with respect to the median plane.

4 . A mold for manufacturing a casting blade preform ( 14 ) according to claim 1 , comprising an internal cavity the three-dimensional shape of which determines, in a form-fitting manner, the three-dimensional shape of the blade preform, with the mold ( 48 ) comprising at least two first ( 50 A, 52 A) and two second ( 54 A, 56 A) blocks arranged in pairs opposite each other along perpendicular axes ( 58 , 60 ), with the first two cavity retainer blocks ( 50 A, 52 A) each comprising a recess ( 50 B, 52 B) having a boss ( 50 C, 52 C) intended to define the inner surface of a plat-form ( 16 ) of the preform and the blade defining, with recesses ( 54 B, 56 B) of the second cavity retainer blocks ( 54 A, 56 A), spaces intended to form upstream and downstream side webs ( 26 , 28 ) for connecting upstream and downstream edges of a plat-form ( 16 ) of the blade preform to the upstream and downstream ends of a blade root, with the first cavity retainer blocks ( 50 A, 52 A) further comprising substantially parallel and opposed faces ( 50 J, 52 J) intended to form flanks of a root part ( 14 ) of the blade preform, characterized in that the recess ( 50 B, 528 ) of each first block ( 50 A, 52 A) comprises first ( 50 H, 52 H) and second surfaces ( 501 , 521 ) on either side of the boss connected to the face ( 50 J, 52 J) forming a flank of the blade root, with the first ( 50 H, 52 H) and the second ( 501 , 521 ) surfaces of the first cavity retainer blocks converging toward the faces of the flanks of the blade root.

5 . A method for manufacturing a turbine blade using the mold according to claim 4 , characterized in that it consists in:
a. positioning the mold ( 48 ) so that the first ( 50 A, 52 A) and second ( 54 A, 56 A) cavity retainer blocks are arranged in an upper position relative to a lower mold part; b. gradually introducing a liquid material into the lower part of the mold so that the liquid level gradually increases inside the mold ( 48 ) and forms a blade preform, in a form-fitting manner; then c. performing a finishing machining of the blade preform to the desired final dimensions of the blade.

Assignees

• Snecma

Inventors

• Congratel Sébastien Serge Francis
• Dupeyre Raphaël Jean Philippe
• Klein Guillaume
• Mathieu David
• Tang Ba-Phuc

Classifications

• F05D2230/21

  by casting · CPC title

• B22C9/06 Primary

  Permanent moulds for shaped castings (moulds for ingots B22D7/06) · CPC title

• B22D25/02

  by its peculiarity of shape; of works of art {(cylinders, pistons B22D15/02)} · CPC title

• F01D5/141

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• B22C9/10 Primary

  Cores; Manufacture or installation of cores {(breaker cores B22C9/084)} · CPC title