Annular one-piece corrugated liner for combustor of a gas turbine engine

• US 20030192320A1
• Filed: 04/10/2002
• Published: 10/16/2003
• Est. Priority Date: 04/10/2002
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Vandike, John L., Devane, Shaun M., Farmer, Gilbert
• Granted Patent: US 6,655,147 B2
• Time in Patent Office: Days
• US Class Current: 60/804
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/50 Combustion chambers comprising an annular flame tube within an annular casing toroidal combustion chambers F23R3/52

Abstract

An annular one-piece liner for a combustor of a gas turbine engine, including a first end adjacent to an upstream end of the combustor, a second end adjacent to a downstream end of the combustor, and a plurality of corrugations between the first and second ends, each corrugation having an amplitude and a wavelength between an adjacent corrugation, wherein the amplitude of the corrugations and/or the wavelength between adjacent corrugations is variable from the first end to the second end.

Claims

1. An annular one-piece liner for a combustor of a gas turbine engine, comprising:

(a) a first end adjacent to an upstream end of said combustor;

(b) a second end adjacent to a downstream end of said combustor; and

,

(c) a plurality of corrugations between said first and second ends, each corrugation having an amplitude and a wavelength between an adjacent corrugation;

wherein the amplitude of said corrugations is variable from said first end to said second end.

2. The liner of claim 1, wherein the amplitude of each corrugation is formed in accordance with a stiffness requirement for said liner at such axial location thereof.

3. The liner of claim 1, wherein the amplitude of corrugations located within a middle section of said liner is greater than the amplitude of corrugations located within a section of said liner adjacent said first end.

4. The liner of claim 1, wherein the amplitude of corrugations located within a middle section of said liner is greater than the amplitude of corrugations located within a section of said liner adjacent said second end.

5. The liner of claim 1, wherein the amplitude of corrugations located within a section of said liner adjacent said first end is not less than the amplitude of corrugations located within a section of said liner adjacent said second end.

6. The liner of claim 1, wherein the wavelength between adjacent corrugations is variable from said first end to said second end.

7. The liner of claim 6, wherein the wavelength between corrugations located within a middle section of said liner is less than the wavelength between corrugations located within a section of said liner adjacent said first end.

8. The liner of claim 6, wherein the wavelength between corrugations located within a middle section of said liner is less than the wavelength between corrugations located within a section of said liner adjacent said second end.

9. The liner of claim 6, wherein the wavelength between corrugations located within a section of said liner adjacent said first end is not greater than the wavelength between corrugations located within a section of said liner adjacent said second end.

10. The liner of claim 1, wherein a buckling margin for said liner is in a range of approximately 35-250 psi.

11. The liner of claim 1, wherein a thickness of said liner is in a range of approximately 0.030-0.080 inches.

12. The liner of claim 1, wherein the total number of corrugations in said liner is in a range of approximately 6-12.

13. The liner of claim 1, wherein material utilized for said liner is among a group including HAST X, HS 188, and HA 230.

14. The liner of claim 1, further comprising a multihole cooling pattern formed in said liner such that a density for each corrugation is relative to the amplitude therefor.

15. The liner of claim 6, further comprising a multihole cooling pattern formed in said liner such that a density for each corrugation is relative to the wavelength between adjacent corrugations.

16. The liner of claim 1, wherein the wavelength between adjacent corrugations is substantially equal.

17. The liner of claim 1, wherein the liner is an outer liner for said combustor.

18. The liner of claim 1, wherein the liner is an inner liner for said combustor.

19. An annular one-piece liner for a combustor of a gas turbine engine, comprising:

(a) a first end adjacent to an upstream end of said combustor;

(b) a second end adjacent to a downstream end of said combustor; and

,

(c) a plurality of corrugations between said first and second ends, each corrugation having an amplitude and a wavelength between an adjacent corrugation;

wherein the wavelength between adjacent corrugations is variable from said first end to said second end.

20. The liner of claim 19, wherein the wavelength between each adjacent pair of corrugations is formed in accordance with a stiffness requirement for said liner at such axial location thereof.

21. The liner of claim 19, wherein the wavelength between corrugations in a middle section of said liner is less than the wavelength between corrugations located in a section of said liner adjacent said first end.

22. The liner of claim 19, wherein the wavelength between corrugations in a middle section of said liner is less than the wavelength between corrugations located in a section of said liner adjacent said second end.

23. The liner of claim 19, wherein the wavelength between corrugations located in a section of said liner adjacent said first end is not greater than the wavelength between corrugations located in a section of said liner adjacent said second end.

24. The liner of claim 19, wherein a buckling margin for said liner is in a range of approximately 35-250 psi.

25. The liner of claim 19, wherein a thickness of said liner is in a range of approximately 0.030-0.080 inches.

26. The liner of claim 19, wherein the total number of corrugations in said liner is in a range of approximately 6-11.

27. The liner of claim 19, wherein material utilized for said liner is among a group including HAST X, HS 188, and HA 230.

28. The liner of claim 19, further comprising a multihole cooling pattern formed in said liner such that a density for each corrugation is relative to the wavelength between adjacent corrugations.

29. The liner of claim 19, wherein the amplitude for each corrugation is substantially equal.

30. The liner of claim 19, wherein the liner is an outer liner for said combustor.

31. The liner of claim 19, wherein the liner is an inner liner for said combustor.