Process for producing a blade for a turbomachine

Patent metadata

Field	Value
Publication number	US-2017260865-A1
Application number	US-201715451529-A
Country	US
Kind code	A1
Filing date	Mar 7, 2017
Priority date	Mar 8, 2016
Publication date	Sep 14, 2017
Grant date	—

Abstract

The invention relates to a method for producing a blade ( 10 ) for a turbo machine, especially for an aviation engine, comprising at least the following steps:
provision of a monocrystalline or polycrystalline basic body ( 14 ) with a supporting surface ( 16 ), and generative construction of a blade airfoil ( 12 ) of the blade ( 10 ) on the supporting surface ( 16 ) by layer-by-layer melting and/or sintering of a metallic and/or ceramic powder consisting of a first material ( 18 ) or material mixture; and separation of the blade airfoil ( 12 ) from the supporting surface ( 16 ) of the basic body ( 14 ) on a parting surface ( 20 ) of the blade airfoil ( 12 ).

A further aspect of the invention relates to a blade which is obtainable and/or is obtained by means of such a method.

First claim

1 .- 12 . (canceled)

13 . A method for producing a blade for a turbomachine, wherein the method comprises:
providing a monocrystalline or polycrystalline basic body having a supporting surface, and generatively constructing a blade airfoil of the blade on the supporting surface by layer-by-layer melting and/or sintering of a metallic and/or ceramic powder of a first material or material mixture; and separating the blade airfoil from the supporting surface of the basic body on a parting surface of the blade airfoil.

14 . The method of claim 13 , wherein separating of the blade airfoil from the supporting surface of the basic body is carried out by erosion.

15 . The method of claim 13 , wherein the method further comprises generatively constructing a blade root of the blade on the parting surface of the blade airfoil and thereby connecting the blade root to the blade airfoil.

16 . The method of claim 15 , wherein the blade root, during generative construction thereof, is produced by layer-by-layer melting and/or sintering of a metallic and/or ceramic powder of a second material or material mixture which is different from the first material or material mixture.

17 . The method of claim 15 , wherein generative construction of the blade root is carried out in such a way that a polycrystalline structure is produced in the blade root.

18 . The method of claim 15 , wherein generative construction of the blade airfoil and/or of the blade root is carried out in a construction chamber which is exposed to a negative pressure.

19 . The method of claim 15 , wherein after connecting, the blade root and the blade airfoil are subjected to a common hot isostatic pressing.

20 . The method of claim 15 , wherein after connecting, the blade root and the blade airfoil are subjected to a common age-annealing.

21 . The method of claim 13 , wherein the first material or material mixture comprises a TiAl alloy.

22 . The method of claim 21 , wherein the TiAl alloy comprises, in addition to Ti and Al, one or more of Nb, Mo, W, Zr, V, Y, Hf, Si, C, Co.

23 . The method of claim 21 , wherein the TiAl alloy comprises
from 30 to 42 at. % Al from 5 to 25 at. % Nb from 2 to 10 at. % Mo from 0.1 to 10 at. % Co or Zr from 0.1 to 1,5 at. % Si, from 0.1 to 0.5 at. % Hf, remainder Ti.

24 . The method of claim 23 , wherein the TiAl alloy comprises from 0.1 to 0.5 at. % Si.

25 . The method of claim 21 , wherein the TiAl alloy comprises
from 30 to 35 at. % Al
from 15 to 25 at. % Nb
from 5 to 10 at. % Mo
from 1 to 10 at. % Co or Zr,
from 0.1 to 0.5 at. % Si
from 0.1 to 0.5 at. % Hf,
remainder Ti.

26 . The method of claim 25 , wherein the TiAl alloy comprises from 32 to 37 at. % Al.

27 . The method of claim 25 , wherein the TiAl alloy comprises from 5 to 10 at. % Co or Zr.

28 . The method of claim 25 , wherein the TiAl alloy comprises from 0.2 to 1.0 at. % Si.

29 . The method of claim 26 , wherein the TiAl alloy comprises from 5 to 10 at. % Co or Zr and from 0.2 to 1.0 at. % Si.

30 . The method of claim 15 , wherein the blade root comprises a second material or material mixture which comprises a TiAl alloy.

31 . The method of claim 30 , wherein the TiAl alloy is a γ-TiAl alloy.

32 . A blade for a turbomachine, wherein the blade has been produced by the method of claim 13 .

Assignees

• MTU Aero Engines AG

Inventors

• Schloffer Martin

Classifications

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• B22F10/38

  to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures · CPC title

• B22F10/64

  by thermal means (control of energy beam parameters for post heating B22F10/364) · CPC title

• B33Y70/00

  Materials specially adapted for additive manufacturing · CPC title

• B33Y70/10

  Composites of different types of material, e.g. mixtures of ceramics and polymers or mixtures of metals and biomaterials · CPC title