Method of fabricating a turbine engine part

Patent metadata

Field	Value
Publication number	US-10793970-B2
Application number	US-201716310238-A
Country	US
Kind code	B2
Filing date	Jun 14, 2017
Priority date	Jun 15, 2016
Publication date	Oct 6, 2020
Grant date	Oct 6, 2020

Abstract

A method of fabricating a turbine engine part, the method including fabricating an ingot out of ceramic material of eutectic composition by performing the Czochralski process including putting a seed of the ingot that is to be obtained into contact with a molten bath of a mixture of eutectic composition in order to initiate the formation of the ingot on the seed, the mixture including at least two ceramic compounds; drawing the ingot from the molten bath while imposing on the ingot that is being formed a drawing speed less than or equal to 10 mm/h together with rotation at a speed of rotation less than or equal to 50 rpm; and machining the ingot as fabricated in this way in order to obtain the turbine engine part.

First claim

The invention claimed is:

1. A method of fabricating a turbine engine part, the method comprising:
fabricating an ingot out of ceramic material of eutectic composition by performing the Czochralski process comprising the following steps:
putting a seed of the ingot that is to be obtained into contact with a molten bath of a mixture of eutectic composition in order to initiate the formation of the ingot on the seed, said mixture comprising at least two ceramic compounds;
drawing the ingot from the molten bath while imposing on the ingot that is being formed a drawing speed less than or equal to 10 mm/h together with rotation at a speed of rotation less than or equal to 50 rpm; and

machining the ingot as fabricated in this way in order to obtain the turbine engine part,
wherein the ingot is drawn from the molten bath along a drawing axis, and wherein a temperature gradient less than or equal to 50° C./mm is maintained in the ingot along the drawing axis, at least in the vicinity of a surface of the molten bath.

2. A method according to claim 1 , wherein the eutectic mixture includes alumina.

3. A method according to claim 1 , wherein the eutectic mixture includes zirconia.

4. A method according to claim 1 , wherein the eutectic mixture includes at least: a rare earth oxide, an aluminum and rare earth garnet RE 3 Al 5 O 12 , or a perovskite REAlO 3 , where RE designates a rare earth element.

5. A method according to claim 1 , wherein the eutectic mixture is selected from the following mixtures: Al 2 O 3 —ZrO 2 , Al 2 O 3 -YAG, RE 3 Al 5 O 12 —Al 2 O 3 where RE is a rare element, Al 2 O 3 —RE 3 Al 5 O 12 —ZrO 2 , and Al 2 O 3 -YAG-ZrO 2 .

6. A method according to claim 1 , wherein the ingot being formed is subjected to a drawing speed lying in the range 1 mm/h to 5 mm/h.

7. A method according to claim 1 , wherein the ingot being formed is subjected to a speed of rotation lying in the range 1 rpm to 30 rpm.

8. A method according to claim 1 , wherein the fabricated part is a turbine engine blade or vane.

9. A method according to claim 1 , wherein the fabricated part is a ring sector.

10. A method according to claim 1 , wherein the fabricated part is a nozzle.

Assignees

• Safran Aircraft Engines
• Safran
• Centre Nat Rech Scient
• Univ Claude Bernard Lyon

Inventors

• Potelle Amélie
• Benamara Omar
• Lebbou Kheirreddine
• Podgorski Michaël

Classifications

• C30B21/06

  by pulling from a melt · CPC title

• C04B35/109

  containing zirconium oxide or zircon (ZrSiO4) · CPC title

• C30B29/28

  with formula A3Me5O12 wherein A is a rare earth metal and Me is Fe, Ga, Sc, Cr, Co or Al, e.g. garnets · CPC title

• C04B35/107 Primary

  Refractories by fusion casting · CPC title

• C30B29/24

  with formula AMeO3, wherein A is a rare earth metal and Me is Fe, Ga, Sc, Cr, Co or Al, e.g. ortho ferrites · CPC title