Hot gas component of a turbomachine including an embedded channel

• US 8,210,815 B2
• Filed: 12/02/2009
• Issued: 07/03/2012
• Est. Priority Date: 12/24/2004
• Status: Expired due to Fees

• Current Assignee: Ansaldo Energia Switzerland AG (Ansaldo Energia SPA)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Bezencon, Cyrille, Fehrmann, Bernd, Hoebel, Matthias, Konter, Maxim, Kurz, Wilfried, Wagnière, Jean-Daniel
• Primary Examiner(s): EDGAR, RICHARD A
• Application Number:
  US12/629,245
• Publication Number:
  US 20100080688A1
• Time in Patent Office: 944 Days
• Field of Search: 416/236.R
• US Class Current: 416/97.R
• CPC Class Codes: B23P 15/02 turbine or like blades from one piece
• CPC Class Codes: B23P 15/04 turbine or like blades from several pieces
• CPC Class Codes: C30B 13/24 using electromagnetic waves
• CPC Class Codes: C30B 29/52 Alloys
• CPC Class Codes: F01D 5/187 Convection cooling

Abstract

A component, especially a hot gas component of a turbomachine, has at least one passage (7, 7′), especially a cooling passage, which is embedded in an outer wall (5) of the component (1) of the turbomachine and basically extends parallel to the surface (6) of the component (1). The component (1) has a basic body (8) and at least one coating (9) which is applied to the basic body on the outside, and the passage (7, 7′) on one hand is formed by a cavity which is formed in the basic body (8), and on the other hand is closed off towards the surface (6) of the component (1) by the coating (9).

Claims

1. A hot gas component of a turbomachine, the component comprising:

a monocrystalline basic body including an outer wall;

a component outer surface;

at least one passage embedded in the outer wall and extending parallel to the component outer surface, which at least one passage is configured and arranged to conduct a cooling medium;

at least one coating on the outer wall of the basic body, the at least one passage formed by a cavity in the basic body closed off towards the outer surface by the at least one coating; and

wherein the at least one coating is formed of a material having a monocrystalline structure which is epitaxially connected to the monocrystalline basic body.

2. The component as claimed in claim 1, wherein the basic body is formed of a nickel-based alloy.

3. The component as claimed in claim 1, wherein the at least one coating comprises the same material as the basic body.

4. The component as claimed in claim 1, wherein the at least one coating is an MCrALY alloy, wherein M is selected from the group consisting of nickel, cobalt, iron, and combinations thereof.

5. The component as claimed in claim 1, further comprising:

a cooling circuit of the turbomachine; and

wherein at least one of the at least one passage is integrated in the turbomachine cooling circuit.

6. The component as claimed in claim 5, further comprising:

at least one discharge opening which leads to the component outer surface; and

wherein the at least passage integrated in the turbomachine cooling circuit is in fluid communication with the at least discharge opening.

7. The component as claimed in claim 1, further comprising:

a thermal protection layer outside of the at least one coating; and

wherein the at least one coating supports the thermal protection layer.

8. The component as claimed in claim 1, wherein the at least one passage comprises a plurality of passages, and wherein the at least one coating extends across and closes off the plurality of passages.

9. The component as claimed in claim 1, wherein the at least one passage defines a passage longitudinal axis at a distance of less than 3 mm from the component outer surface.

10. The component as claimed in claim 1, wherein the at least one passage comprises a plurality of passages in fluid communication and together forming a communicating passage network.

11. The component as claimed in claim 1, wherein a length-to-diameter ratio of the at least one passage is greater than 5.

12. The component as claimed in claim 1, wherein a width of the cavity is less than 1 mm.

13. The component as claimed in claim 12, wherein the width of the cavity is between 0.02 mm and 0.5 mm.

14. The component as claimed in claim 13, wherein the width of the cavity is between 0.1 mm to 0.3 mm.

15. The component as claimed in claim 1, wherein the width of the cavity tapers outwardly.

16. The component as claimed in claim 1, wherein the component comprises a blade or a thermal protection element of a turbine.

17. The component as claimed in claim 1, wherein the at least one passage defines a passage longitudinal axis at a distance of less than 1 mm from the component outer surface.

18. A hot gas component of a turbomachine formed by a method comprising:

forming at least one passage-like cavity in a basic body of the component;

covering the at least one passage-like cavity by applying a coating material to the basic body;

locally surface melting the basic body at least on two sides of the cavity simultaneous with said applying and with melting the coating material at least in the region of the cavities, wherein the coating material, a process temperature, and the width of the cavity are matched to each other so that the molten coating material does not penetrate into the cavity on account of surface tension; and

cooling and hardening the molten coating material so that the coating material is epitaxially built up on the basic body, achieving a metallurgical connection to the basic body on the two sides of the cavity.

19. The hot gas component as claimed in claim 18, wherein said simultaneous melting of the basic body and said applying of the coating material comprises a process selected from the group consisting of plasma spraying, electron beam evaporation, lasering, and combinations thereof.

20. The hot gas component as claimed in claim 19, further comprising:

feeding the coating material in the form of powder or wire.

21. The hot gas component as claimed in claim 18, wherein forming at least one passage-like cavity comprises a process selected from the group consisting of precision investment casting, mechanically forming, electrochemically forming, photochemically forming, laser forming, and combinations thereof.

22. The hot gas component as claimed in claim 18, wherein:

a first phase of the hardening of the coating material is of the γ

-type, or

in the coating, a transition from the monocrystal structure to the equiaxial structure is avoided, or

in the coating, the formation of new crystallization germs is avoided, or

combinations thereof.

23. The hot gas component as claimed in claim 18, further comprising:

smoothing the surface of the coating after said cooling and hardening by laser melting.

24. The hot gas component as claimed in claim 18, further comprising:

heating the basic body before and/or during said coating, to reduce stresses which occur by the hardening and/or cooling of the coating.

25. The hot gas component as claimed in claim 18, wherein applying the coating comprises applying so that the coating contains a monocrystalline structure and/or is epitaxially connected to the basic body.

26. The hot gas component as claimed in claim 18, further comprising:

additionally melting the coating material so that a monocrystal structure of the basic body is reproduced in the coating and/or a polycrystalline structure of the coating is transformed into a monocrystal structure.

27. The hot gas component as claimed in claim 19, wherein lasering comprises an epitaxial laser metal forming process.

28. The hot gas component as claimed in claim 18, further comprising:

processing the coating after said cooling and hardening so that the coating contains a monocrystalline structure and/or is epitaxially connected to the basic body.