Combustor for gas turbine engine and method of manufacture

Patent metadata

Field	Value
Publication number	US-11549437-B2
Application number	US-202117178418-A
Country	US
Kind code	B2
Filing date	Feb 18, 2021
Priority date	Feb 18, 2021
Publication date	Jan 10, 2023
Grant date	Jan 10, 2023

Abstract

A combustor for a gas turbine engine includes an outer liner having a first end interconnected to an opposite second end by an outer liner wall composed of a plurality of outer segments. The inner liner has a first inner end interconnected to an opposite second inner end by an inner liner wall composed of a plurality of inner segments. The outer liner wall and the inner liner wall define a combustion chamber, and each of the outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis. The outer wall segments includes a first segment, a second segment that extends at a second angle relative to the first segment, which is less than a third angle defined between the second segment and a third segment and is substantially the same as a fourth angle defined between the third segment and a fourth segment.

First claim

What is claimed is:

1. A combustor for a gas turbine engine, comprising:
an outer liner having a first end and a second end opposite the first end, the first end interconnected to the second end by an outer liner wall composed of a plurality of outer wall segments; and
an inner liner having a first inner end and a second inner end opposite the first inner end, the second inner end coupled to the second end of the outer liner, the first inner end interconnected to the second inner end by an inner liner wall composed of a plurality of inner wall segments,
wherein the outer liner wall and the inner liner wall cooperate with each other to define a combustion chamber, and each of the plurality of outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis of the combustor and the plurality of outer wall segments includes a first straight wall segment, a second straight wall segment that extends at a second angle relative to the first straight wall segment, which is less than a third angle defined between the second straight wall segment and a third straight wall segment of the plurality of outer wall segments and is substantially the same as a fourth angle defined between the third straight wall segment and a fourth straight wall segment of the plurality of outer wall segments, and each of the second angle and the fourth angle is an acute angle.

2. The combustor of claim 1 , wherein the first straight wall segment of the plurality of outer wall segments is at the first end of the outer liner.

3. The combustor of claim 1 , wherein at least one of the outer liner wall and the inner liner wall has a double wall, with an effusion cooling system defined between the double wall.

4. The combustor of claim 1 , wherein the fourth angle is different than a fifth angle defined between the fourth straight wall segment and a fifth straight wall segment of the plurality of outer wall segments.

5. The combustor of claim 4 , wherein the first straight wall segment, the second straight wall segment, the third straight wall segment, the fourth straight wall segment and the fifth straight wall segment are each integrally formed.

6. The combustor of claim 5 , further comprising a sixth straight wall segment, and the sixth straight wall segment cooperates with the inner liner to define a passageway to an outlet of the combustor.

7. The combustor of claim 1 , wherein each of the plurality of inner wall segments extends at an angle of at least 40 degrees relative to the longitudinal axis.

8. The combustor of claim 7 , wherein the plurality of inner wall segments includes a first straight inner wall segment and a second straight inner wall segment, and the second straight inner wall segment extends at a tenth angle relative to the first straight inner wall segment, and the tenth angle is an acute angle.

9. The combustor of claim 8 , wherein the plurality of inner wall segments includes a third straight inner wall segment that extends at an eleventh angle relative to the second straight inner wall segment, and the eleventh angle is different than the tenth angle.

10. The combustor of claim 9 , wherein the plurality of inner wall segments includes a fourth straight inner wall segment that extends at a twelfth angle relative to the third straight inner wall segment, and the twelfth angle is different than the tenth angle.

11. The combustor of claim 10 , wherein the plurality of inner wall segments includes a fifth straight inner wall segment that extends at a thirteenth angle relative to the third straight inner wall segment, and the thirteenth angle is different than the twelfth angle.

12. The combustor of claim 1 , wherein the third straight wall segment defines at least one fuel injector hole.

13. A method of manufacturing a combustor for a gas turbine engine, comprising:
forming an outer liner having a first end, a second end opposite the first end and an outer liner wall interconnecting the first end and the second end, the outer liner wall including a plurality of outer wall segments that each extend at an angle of at least 40 degrees relative to a longitudinal axis of the combustor, the plurality of outer wall segments including a first straight wall segment, a second straight wall segment that extends at a second angle relative to the first straight wall segment, which is less than a third angle defined between the second straight wall segment and a third straight wall segment of the plurality of outer wall segments and is substantially the same as a fourth angle defined between the third straight wall segment and a fourth straight wall segment of the plurality of outer wall segments, and each of the second angle and the fourth angle is an acute angle;
substantially concurrently with the forming of the outer liner, forming an inner liner nested within the outer liner wall, the inner liner having a first inner end and a second inner end opposite the first inner end, the first inner end interconnected to the second inner end by an inner liner wall composed of a plurality of inner wall segments; and
coupling the second inner end of the inner liner to the second end of the outer liner to define a combustion chamber.

14. The method of claim 13 , wherein the forming of the outer liner and the forming of the inner liner further comprise additively manufacturing the outer liner and the inner liner and the longitudinal axis of the combustor is coaxial with a build direction of the combustor during the additive manufacturing.

15. The method of claim 13 , wherein the forming of the inner liner further comprises the plurality of inner wall segments to each extend at an angle of at least 40 degrees relative to the longitudinal axis of the combustor.

16. The method of claim 13 , wherein the coupling the second inner end of the inner liner to the second end of the outer liner further comprises welding the second inner end of the inner liner to the second end of the outer liner.

17. The method of claim 13 , wherein the forming the outer liner further comprises forming the outer liner with a double wall and an effusion cooling system defined within the double wall.

18. The method of claim 13 , further comprising forming an additional wall segment and coupling the additional wall segment to the first straight wall segment of the outer liner.

19. A combustor for a gas turbine engine, comprising:
an outer liner having a first end and a second end opposite the first end, the first end interconnected to the second end by an outer liner wall composed of a plurality of outer wall segments; and
an inner liner having a first inner end and a second inner end opposite the first inner end, the second inner end coupled to the second end of the outer liner, the first inner end interconnected to the second inner end by an inner liner wall composed of a plurality of inner wall segments,
wherein the outer liner wall and the inner liner wall cooperate with each other to define a combustion chamber, and each of the plurality of outer wall segments and the plurality of inner wall segments extends at an angle of at least 40 degrees relative to a longitudinal axis of the combustor and the plurality of outer wall segments includes a first straight wall segment that extends along a first axis that is substantially perpendicular to the longitudinal axis, a second straight wall segment that extends along a second axis that is transverse to the first axis and to the longitudinal axis, a third straight wall segment that extends along a third axis that is substantially parallel to t

Assignees

• Honeywell Int Inc

Inventors

• Dudebout Rodolphe
• Ozogul Hamdullah
• Verma Atul
• Kujala Amy
• Wedig Michael
• Meyer Ryan
• Culbertson Bradley

Classifications

• F05D2230/31

  Layer deposition · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title