Laminated airfoil for a gas turbine

Patent metadata

Field	Value
Publication number	US-2019055849-A1
Application number	US-201515770842-A
Country	US
Kind code	A1
Filing date	Nov 10, 2015
Priority date	Nov 10, 2015
Publication date	Feb 21, 2019
Grant date	—

Abstract

An airfoil (30) for a gas turbine (10) wherein the airfoil (30) includes an outer wall (32) having leading (34) and trailing (36) edges and convex (40) and concave (38) surfaces and wherein the outer wall (32) forms an internal cavity (52). The airfoil (30) includes at least one inner layer (42) located within the cavity (52), wherein the inner layer (42) has a shape that corresponds to the shape of the outer wall (32). The airfoil (30) also includes a leading edge insert (58) located adjacent the leading edge (34) of the outer wall (32). Further, the airfoil (30) includes a trailing edge insert (60) located adjacent the trailing edge (36) of the outer wall (32) wherein the at least one inner layer (42) is bonded to an inside surface (56) of the outer wall (32) to encapsulate the leading (58) and trailing (60) edge inserts.

First claim

What is claimed is:

1 . An airfoil for a gas turbine, comprising;
an outer wall having leading and trailing edges and convex and concave surfaces, wherein the outer wall forms an internal cavity; at least one inner layer located within the cavity; and at least one insert located in the cavity, wherein the at least one inner layer is bonded to an inside surface of the outer wall to encapsulate the at least one insert.

2 . The airfoil according to claim 1 , wherein the at least one insert includes leading and trailing edge inserts.

3 . The airfoil according to claim 1 , wherein the at least one insert includes a mid-span insert.

4 . The airfoil according to claim 3 , wherein at least one layer includes a second layer for encapsulating the mid-span insert.

5 . The airfoil according to claim 2 , wherein the at least one insert includes first and second interior inserts.

6 . The airfoil according to claim 1 , wherein the at least one inner layer is bonded to the inside surface of the outer wall by explosive welding.

7 . The airfoil according to claim 1 , wherein the at least one insert includes a solid material, metallic foam, or lattice structure.

8 . The airfoil according to claim 1 , wherein the at least one insert includes at least one cooling passage.

9 . An airfoil for a gas turbine, comprising;
an outer wall having leading and trailing edges and convex and concave surfaces, wherein the outer wall forms an internal cavity; at least one inner layer located within the cavity, wherein the inner layer has a shape that corresponds to the shape of the outer wall; a leading edge insert located adjacent the leading edge of the outer wall; and a trailing edge insert located adjacent the trailing edge of the outer wall wherein the at least one inner layer is bonded to an inside surface of the outer wall to encapsulate the leading and trailing edge inserts.

10 . The airfoil according to claim 9 , wherein the airfoil further includes a mid-span insert.

11 . The airfoil according to claim 10 , wherein at least one layer includes a second layer for encapsulating the mid-span insert.

12 . The airfoil according to claim 9 , wherein the airfoil includes further first and second interior inserts.

13 . The airfoil according to claim 9 , wherein the at least one inner layer is bonded to the inside surface of the outer wall by explosive welding.

14 . The airfoil according to claim 9 , wherein the leading and trailing edge inserts include a solid material, metallic foam, or lattice structure.

15 . The airfoil according to claim 9 , wherein the leading and trailing edge inserts include at least one cooling passage.

16 . A method for fabricating an airfoil for a gas turbine, comprising;
providing an outer wall having leading and trailing edges and convex and concave surfaces, wherein the outer wall forms an internal cavity; providing at least one inner layer located within the cavity; providing at least one insert located in the cavity; and bonding the at least one inner layer to an inside surface of the outer wall to encapsulate the at least one insert.

17 . The method according to claim 16 , wherein the at least one insert includes leading and trailing edge inserts.

18 . The method according to claim 16 , wherein the at least one insert includes a mid-span insert.

19 . The method according to claim 16 , wherein the at least one insert includes first and second interior inserts.

20 . The method according to claim 16 , wherein the at least one inner layer is bonded to the inside surface of the outer wall by explosive welding.

Assignees

• Siemens Ag

Inventors

• James Allister William

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2240/12

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

• F05D2230/21

  by casting · CPC title