Assembly for gas turbine engine

Inventors: Cameron W. Farley (Fort Thomas, KY); Michael Alan Stieg (Orlando, FL); Jason David Shapiro (Methuen, MA); Gregory Scott Phelps (Cincinnati, OH); Gregory Allen Willis (Cincinnati, OH); Jerome Geoffrey Magnant (Rexford, NY); Benjamin Wenning (Springboro, OH)

Assignee: General Electric Company

F01D9/041 F05D2300/6033

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Quick Facts

Patent No.: US 12704072
App. No.: 19/296,141
Granted: Aug 11, 2026
Kind: B1

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Abstract

An assembly for a gas turbine engine, the assembly including a plurality of assembly segments connected in a 360 degree arrangement, each assembly segment of the plurality of assembly segments including a first band, a second band, a first vane extending from the first band to the second band, the first vane being single-formed with the first band and the second band, and a second vane extending from the first band to the second band, wherein the second vane is joined to the first band with a first joint, and the second vane is joined to the second band with a second joint.

Claims (26)

1 . An assembly for a gas turbine engine, the assembly comprising:

a plurality of assembly segments connected in a 360 degree arrangement, each assembly segment of the plurality of assembly segments comprising:

a first band;

a second band;

a first vane extending from the first band to the second band, the first vane being single-formed with the first band and the second band; and

a second vane extending from the first band to the second band,

wherein the second vane is joined to the first band with a first joint, and the second vane is joined to the second band with a second joint.

2 . The assembly of claim 1 , wherein the first band defines a leading edge and a trailing edge, the leading edge defining a leading circumferential length and the trailing edge defining a trailing circumferential length, wherein the leading circumferential length is smaller than the trailing circumferential length.

3 . The assembly of claim 2 , wherein the second band defines a leading edge and a trailing edge, wherein the trailing edge of the first band and the trailing edge of the second band define a nozzle.

4 . The assembly of claim 3 , wherein the leading edge of the first band and the leading edge of the second band define a turbine center frame.

5 . The assembly of claim 2 , wherein the trailing edge of the first band is outward from the leading edge of the first band in a radial direction.

6 . The assembly of claim 1 , wherein the second band defines a leading edge and a trailing edge, the leading edge defining a leading circumferential length and the trailing edge defining a trailing circumferential length, wherein the leading circumferential length is smaller than the trailing circumferential length.

7 . The assembly of claim 1 , wherein the first band, the first vane, and the second vane are formed of a ceramic matrix composite (CMC) material.

8 . The assembly of claim 1 , wherein the first joint or the second joint is one of a slurry, a fillet, a cap, or a noodle.

9 . The assembly of claim 1 , wherein the first band defines a void, the second band defines a pocket, and the second vane defines a first end disposed in the void and a second end disposed in the pocket.

10 . The assembly of claim 9 , wherein the first joint includes a bonding material extending from the first band to the first end of the second vane.

11 . The assembly of claim 9 , wherein the second joint includes a bonding material disposed in the pocket and extending from the second band to the second end of the second vane.

12 . The assembly of claim 1 , wherein the first vane defines a slot extending from the first band to the second band.

13 . The assembly of claim 1 , wherein the second vane is solid.

14 . The assembly of claim 1 , wherein the second vane defines a tapered edge.

15 . The assembly of claim 14 , wherein the first band defines a pocket with a tapered surface, and the tapered edge of the second vane is joined to the tapered surface of the pocket with a bonding material.

16 . The assembly of claim 1 , wherein the plurality of assembly segments define a turbine vane frame assembly, the turbine vane frame assembly including an outer band comprising the first band of each of the plurality of assembly segments and an inner band comprising the second band of each of the plurality of assembly segments.

17 . The assembly of claim 16 , wherein the outer band defines a leading edge and a trailing edge, wherein the trailing edge is disposed outward of the leading edge in a radial direction.

18 . The assembly of claim 17 , wherein the inner band defines a leading edge and a trailing edge, wherein the trailing edge is disposed outward of the leading edge in the radial direction.

19 . The assembly of claim 16 , wherein the outer band and the inner band define a flowpath from a core duct to a low pressure turbine.

20 . The assembly of claim 16 , wherein a pitch angle of the respective first vane of each of the plurality of assembly segments is a same angle.