Turbine engine blade preform

Patent metadata

Field	Value
Publication number	US-9833834-B2
Application number	US-201414895777-A
Country	US
Kind code	B2
Filing date	Jun 4, 2014
Priority date	Jun 5, 2013
Publication date	Dec 5, 2017
Grant date	Dec 5, 2017

Abstract

A blade preform includes a strut connecting a plat-form to a blade root portion extending longitudinally in an upstream-downstream direction, an upstream web and a downstream 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 and downstream webs connect the upstream and downstream ends of the plat-form to the upstream and downstream ends of the blade root. The blade root 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 and the side edges of each web are extended by walls that converge at the flanks of the blade root.

First claim

The invention claimed is:

1. A turbine engine blade preform, with the preform comprising a strut connecting a plat-form to a blade root portion extending longitudinally in an upstream-downstream direction, an upstream web and a downstream web, which each extends in a direction perpendicular to a longitudinal direction of the blade root and are formed at upstream and downstream ends of the strut, with such upstream and downstream webs connecting the upstream and downstream ends of the plat-form to the upstream and downstream ends of the blade root, characterized in that the blade root 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 extend in said longitudinal direction and in that the upstream and downstream webs each comprises two side edges which are extended by converging walls at flanks of the blade root.

2. The preform according to claim 1 , wherein said converging walls are formed by plane faces inclined with respect to a median plane of the blade root extending longitudinally along an upstream/downstream direction.

3. The preform according to claim 2 , wherein the plane faces are inclined at an angle of approximately 45° with respect to the median plane of the blade root.

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

5. The method for manufacturing a turbine blade using the mold according to claim 4 , the method comprising:
a. positioning the mold so that the first and second 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 a liquid level gradually increases inside the mold and forms a blade preform, in a form-fitting manner; and then
c. performing a finishing machining of the blade preform to obtain 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

• 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

• F05D2230/21

  by casting · CPC title

• F01D5/141

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

• F05D2230/61

  using limited numbers of standard modules which can be adapted by machining · CPC title