Method for making a double-wall airfoil

• US 5,640,767 A
• Filed: 01/03/1995
• Issued: 06/24/1997
• Est. Priority Date: 01/03/1995
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: LaChapelle, Donald George, Rowe, Raymond Grant, Jackson, Melvin Robert, Wilson, Paul Stuart, Skelly, David William
• Primary Examiner(s): Cuda, Irene
• Assistant Examiner(s): BUTLER, MARC WINSTON
• Application Number:
  US08/368,511
• Time in Patent Office: 903 Days
• Field of Search: 29/889.721, 29/527.6, 29/527.2, 29/527.4, 29/530, 29/458, 29/460, 29/424, 164/46, 118/427
• US Class Current: 29/889.721
• CPC Class Codes: B23P 15/04 turbine or like blades from several pieces
• CPC Class Codes: C23C 14/02 Pretreatment of the material to be coated C23C14/04 takes precedence
• CPC Class Codes: C23C 14/16 on metallic substrates or on substrates of boron or silicon
• CPC Class Codes: C23C 14/5873 Removal of material
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49341 with cooling passage
• CPC Class Codes: Y10T 29/49986 Subsequent to metal working
• CPC Class Codes: Y10T 29/49989 Followed by cutting or removing material

Abstract

A method for making double-wall airfoil for applications such as the blades and vanes of gas turbine engines by depositing an airfoil skin over an inner support wall which is separately formed and contains channels filled by a channel filling means. The channel filling means is removed thereby forming integral channels within the double-wall for circulating a cooling gas adjacent to the airfoil skin. The airfoil skin deposited may be a metal alloy skin or a microlaminate structure, including microlaminate composite structures.

Claims

1. A method of making a double-wall airfoil, comprising the steps of:

forming a partially-hollow airfoil support wall that is attached to and extends longitudinally from an airfoil base and has an airfoil-shaped outer surface, said support wall formed from a first material and having at least one longitudinally-extending recessed channel formed in the airfoil-shaped outer surface;

filling the at least one longitudinally-extending recessed channel with a channel filling means so as to make an upper surface of the channel filling means substantially continuous with the airfoil-shaped outer surface;

depositing an airfoil skin of a second material, the second material comprising a material selected from the group consisting of;

an I_S /M composite in the form of a micro-laminate having a plurality of alternating layers of I_S and M and an I_S /I_M composite in the form of a micro-laminate having a plurality of alternating layers of I_S and I_M, onto the airfoil-shaped outer surface of the airfoil support wall such that the airfoil skin conforms to the airfoil-shaped outer surface of the support wall and covers the at least one longitudinally-extending recessed channel and the channel filling means, and such that the airfoil skin is metallurgically bonded to the airfoil-shaped outer surface of the airfoil support wall, wherein the combination of the airfoil skin and airfoil support wall form a double-wall airfoil structure; and

removing the channel filling means, thereby creating an integral internal channel within the double-wall airfoil structure.

2. The method of claim 1, wherein the first material comprises a metal ahoy, an I_S /M composite or an I_S /I_M composite.

3. The method of claim 1, wherein the first material is a metal alloy that is formed by casting having a single crystal or directionally solidified microstructure.

4. The method of claim 1, wherein the second material is deposited by the methods comprising physical vapor deposition, chemical vapor deposition, thermal spraying or plating.

5. The method of claim 1, wherein the second material is deposited by being evaporated through a molten pool of another material.

6. The method of claim 1, wherein the first material is from a group consisting of Ni-base superalloys containing both γ

and γ

phases and NiAl intermetallic alloys, and the second material is from a group consisting of Ni-base superalloys containing γ and

γ

phases, NiAl intermetallic alloys, I_S /M composites, and I_S /I_M composites.

7. The method of claim 6, wherein the second material is an I_S /M composite comprising an I_S from a group consisting of Ni₃ [Ti,Ta,Nb,V],NiAl, Cr₃ Si, [Cr,Mo]_X Si, [Ta,Ti,Nb,Hf,Zr,V]C, Cr₃ C₂ and Cr₇ C₃ intermetallic compounds and intermediate phases and an M of a Ni-base superalloy comprising a mixture of both γ

and γ

phases.

8. The method of claim 7, wherein the I_S /M composite is a micro-laminate comprising a plurality of alternating layers of I_S and M.

9. The method of claim 6, wherein the second material is an I_S /I_M composite comprising an I_S from a group consisting of Ni₃ [Ti,Ta,Nb,V],NiAl, Cr₃ Si, [Cr,Mo]_X Si, [Ta,Ti,Nb,Hf, Zr, V]C, Cr₃ C₂ and Cr₇ C₃ intermetallic compounds and intermediate phases and an I_M of an Ni₃ Al intermetallic compound.

10. The method of claim 9, wherein the I_S /I_M composite is a micro-laminate comprising a plurality of alternating layers of I_S and I_M.

11. The method of claim 1, wherein the first material is an Nb-base alloy and the second material is an I_S /M composite comprising an I_S from a group consisting of Nb-containing intermetallic compounds, Nb-containing carbides and Nb-containing borides and an M of an Nb-base alloy.

12. The method of claim 11, wherein the I_S /M composite comprises an M of an Nb-base alloy containing Ti such that the atomic ratio of the Ti to Nb (Ti/Nb) of the alloy is in the range of 0.2-1, and an I_S from a group consisting of Nb-base silicides, Cr₂ [Nb, Ti, Hf], and Nb-base aluminides, and wherein Nb is the primary constituent of Cr₂ [Nb, Ti, Hf] on an atomic basis.

13. The method of claim 12, wherein the at least one channel is formed integrally during the formation of the airfoil support wall.

14. The method of claim 13, wherein the step of forming the airfoil support wall having at least one channel comprises a separate step of forming the recessed channel.

15. The method of claim 14, wherein the step of forming the recessed channel comprises machining or etching.

16. The method of claim 1, wherein the channel filling means is from the group consisting of metal alloys, ceramics, metal alloy/ceramic mixtures or polymers.

17. The method of claim 16, wherein the channel filling means is a metal alloy comprising Cu in the range of 25-35 percent by weight, with a balance of nickel.

18. The method of claim 1, wherein the channel filling means is adapted so as to conform to the recessed channels during the step of depositing the airfoil skin over the temperature range from room temperature up through a maximum temperature experienced during vapor deposition.

19. The method of claim 1, wherein the step of removing the channel filling means is done by melting/extraction or etching.