Method for producing a rotor vane for a turbomachine

Patent metadata

Field	Value
Publication number	US-2016016227-A1
Application number	US-201414771785-A
Country	US
Kind code	A1
Filing date	Mar 4, 2014
Priority date	Mar 7, 2013
Publication date	Jan 21, 2016
Grant date	—

Abstract

The invention relates to a method for producing a rotor vane ( 10 ) for a turbomachine, comprising a step consisting in producing a rough casting, the heel of which has a downstream lip ( 121 ) with a transverse increased thickness ( 130 ) such that the lip has an upstream surface ( 134 ) substantially parallel to the above-mentioned axis, said method comprising an additional step of machining said increased thickness so that the downstream lip has an upstream surface ( 138 ) inclined in relation to the above-mentioned axis.

First claim

1 . Method for producing a rotor blade for a turbine engine, said blade comprising a vane which is connected at one end to a root and at the opposite end thereof to a heel bearing upstream and downstream knife-edge seals, which are inclined at least in part relative to the longitudinal axis (X) of the blade, the method comprising a step which consists in producing a blank casting which is to be machined, wherein the downstream knife-edge seal is formed by casting having a transverse machining allowance in such a way that said knife-edge seal has an upstream face which is substantially parallel to the above-mentioned axis, and in that the method comprises an additional step which consists in machining said machining allowance so that the downstream knife-edge seal has an upstream face which is inclined relative to the above-mentioned axis.

2 . Method according to claim 1 , wherein the knife-edge seals are produced by casting using a mould which, after solidification of the knife-edge seals, is removed from the blade by moving it in translation towards the outside in a direction which is substantially parallel to the longitudinal axis (X) of the blade.

3 . Method according to claim 1 , wherein the machining is carried out using a grinding wheel.

4 . Method according to claim 1 , wherein the knife-edge seals have different angles of inclination relative to the above-mentioned axis.

5 . Method according to claim 1 , wherein said upstream face extends over substantially the entire axial dimension of the downstream knife-edge seal.

6 . Method according to claim 1 , wherein the blank casting is made of an anisotropic material, in particular a nickel-based material.

7 . Mould for carrying out casting of the upstream and downstream knife-edge seals of the heel of a turbine engine rotor blade, comprising a first cavity for forming the upstream knife-edge seal and a second cavity for forming the downstream knife-edge seal, the cavities opening onto a substantially planar face of the mould which is intended to define an outer face of the heel of the blade, wherein the first cavity comprises a downstream face which is inclined relative to a normal to said planar face, and the second cavity comprises an upstream face which is substantially parallel to said normal.

8 . Blank casting which is to be machined to produce a turbine engine rotor blade, comprising a vane which is connected at one end to a root and at the opposite end thereof to a heel bearing upstream and downstream knife-edge seals, the upstream knife-edge seal being inclined at least in part relative to the longitudinal axis of the blade, wherein the downstream knife-edge seal comprises an upstream face which is substantially parallel to the above-mentioned axis and a downstream face which is inclined relative to said axis.

9 . Blank casting according to claim 8 , wherein the upstream knife-edge seal is inclined by an angle of approximately 30° relative to the above-mentioned axis, and the downstream face of the downstream knife-edge seal is inclined by an angle of approximately 15° relative to said axis.

10 . Blank casting according to claim 8 , wherein said knife-edge seals are interconnected by a material web.

Assignees

• Snecma

Inventors

• Klein Guillaume
• Bassery Josserand
• Congratel Sebastien
• Dupeyre Raphael
• Mathieu David
• Tang Ba-Phuc

Classifications

• F01D5/225

  by shrouding · CPC title

• B23P15/02

  turbine or like blades from one piece · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• B22D25/02 Primary

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

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title