Ceramic matrix composite nozzle mounted with a strut and concepts thereof

Patent metadata

Field	Value
Publication number	US-11092023-B2
Application number	US-201815885069-A
Country	US
Kind code	B2
Filing date	Jan 31, 2018
Priority date	Dec 18, 2014
Publication date	Aug 17, 2021
Grant date	Aug 17, 2021

Abstract

A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.

First claim

The invention claimed is:

1. A nozzle segment assembly, comprising:
an outer support ring and an inner support ring;
a nozzle fairing formed of a low coefficient of thermal expansion material having an outer band, an inner band, and a vane extending between said outer band and said inner band; and
a metallic strut extending between said outer support ring and said inner support ring, said metallic strut allowing for load transfer between said nozzle fairing and said metallic strut,
wherein said metallic strut extends through said nozzle fairing and allows radial growth of said metallic strut through said vane, and
wherein said outer band of said nozzle fairing is positioned to engage with and transfer load to said outer support ring or said inner band of said nozzle fairing is positioned to engage with and transfer load to said inner support ring.

2. The nozzle segment assembly of claim 1 , wherein said outer support ring and said inner support ring are 360 degree rings.

3. The nozzle segment assembly of claim 1 , wherein said outer support ring and said inner support ring are arcuate segments.

4. The nozzle segment assembly of claim 1 , wherein at least one of said outer support ring and said inner support ring are supported by a static structure.

5. The nozzle segment assembly of claim 4 , wherein said at least one of said outer support ring and said inner support ring is supported in a cantilevered arrangement from said static structure.

6. The nozzle segment assembly of claim 4 , wherein at least one of said outer support ring and said inner support ring are supported at an axial end.

7. The nozzle segment assembly of claim 1 , wherein said metallic strut is connected to at least one of said inner support ring and said outer support ring by bolting, fastening, capturing, or being integrally formed.

8. The nozzle segment assembly of claim 1 , wherein a radial position of said nozzle fairing is captured between said outer support ring and inner support ring.

9. The nozzle segment assembly of claim 8 , further comprising an interface at a lower end of said metallic strut that extends into a collar of said inner support ring.

10. The nozzle segment assembly of claim 8 , further comprising a pin joint at one of said inner support ring and said outer support ring.

11. The nozzle segment assembly of claim 1 , further comprising a flowpath through said nozzle segment assembly, wherein said flowpath further comprises at least one cavity extending through said vane of said nozzle fairing.

12. The nozzle segment assembly of claim 11 , wherein said flowpath further comprises at least one cavity extending through said metallic strut and in flow communication with said cavity of said nozzle fairing.

13. The nozzle segment assembly of claim 12 , wherein said metallic strut has a plurality of cooling holes for impingement air on an interior surface of said vane.

14. The nozzle segment assembly of claim 13 , wherein said vane of said nozzle fairing has a plurality of cooling film holes in flow communication with said flowpath, wherein said flowpath is further in flow communication with said inner band.

15. The nozzle segment assembly of claim 1 , wherein said vane is integrally formed with said outer band and said inner band.

16. The nozzle segment assembly of claim 15 , wherein the nozzle fairing is unattached to the outer support ring and the inner support ring such that the nozzle fairing floats along a radial direction.

17. The nozzle segment assembly of claim 16 , wherein a radial position of said nozzle fairing is captured between said outer support ring and inner support ring.

18. The nozzle segment assembly of claim 1 , wherein the vane is unattached to the outer support ring and the inner support ring such that the vane floats along a radial direction.

19. The nozzle segment assembly of claim 1 , wherein said nozzle fairing has a stud positioned to allow transfer of load from said nozzle fairing to said outer support ring or said inner support ring.

20. The nozzle segment assembly of claim 1 , wherein said nozzle fairing makes direct contact with said inner support ring or said outer support ring.

Assignees

• Gen Electric

Inventors

• Huizenga Benjamin Scott
• Glynn Christopher Charles
• Senile Darrell Glenn
• Frederick Robert Alan
• Radwanski Michael Todd
• Tuertscher Michael Ray
• Phelps Greg Scott

Classifications

• F01D9/041 Primary

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

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D9/047 Primary

  Nozzle boxes · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F01D9/045 Primary

  for radial flow machines or engines · CPC title