Gas turbine engine wave geometry combustor liner panel

Patent metadata

Field	Value
Publication number	US-10508808-B2
Application number	US-201414893781-A
Country	US
Kind code	B2
Filing date	Jun 12, 2014
Priority date	Jun 14, 2013
Publication date	Dec 17, 2019
Grant date	Dec 17, 2019

Abstract

A panel for a combustor of a gas turbine engine includes a cold side defining at least one convex portion and at least one concave portion. The concave portion is in communication with a passage. A method of operating a combustor section of a gas turbine engine includes: directing an impingement flow toward a multiple of peaks on a cold side of a panel; directing the impingement flow from the multiple of peaks toward a multiple of troughs with a multiple of entrances on the cold side of the panel; and directing the impingement flow through the multiple of entrances and a respective multiple of effusion passages through the panel.

First claim

What is claimed is:

1. A combustor of a gas turbine engine comprising:
a shell comprising a multiple of impingement flow passages; and
a panel mounted to said shell, said panel defining a wave pattern on a cold side thereof, said wave pattern comprising a multiple of peaks and troughs, said troughs defining a multiple of corresponding entrances to a respective multiple of effusion passages through said panel;
wherein at least one of said multiple of impingement flow passages is directed at one of said multiple of peaks; and
wherein each of said entrances is located in a lowest portion of said multiple of troughs.

2. The combustor as recited in claim 1 , wherein said wave pattern is skewed.

3. The combustor as recited in claim 1 , wherein said wave pattern includes a plurality of transverse ridges.

4. The combustor as recited in claim 3 , wherein
each entrance is separated from each other entrance longitudinally by adjacent peaks of the multiple of peaks and laterally by adjacent transverse ridges of the plurality of transverse ridges.

5. The combustor as recited in claim 1 , wherein the wave pattern is continuous.

6. The combustor as recited in claim 1 , wherein the multiple of troughs and the multiple of peaks are integrally formed adjacent one another from a common surface of the cold side.

7. The combustor as recited in claim 1 , wherein each of said multiple of impingement flow passages is directed at a respective one of said multiple of peaks.

8. A combustor of a gas turbine engine comprising:
a shell comprising a multiple of impingement flow passages; and
a panel mounted to said shell, said panel defining a wave pattern on a cold side thereof, said wave pattern including a multiple of peaks and troughs, said troughs defining a multiple of corresponding entrances to a respective multiple of effusion passages through said panel;
wherein each of said multiple of impingement flow passages is directed at a respective one of said multiple of peaks;
wherein each of said entrances is located in a lowest portion of the multiple of troughs; and
wherein said wave pattern is circumferentially arranged about the combustor and is skewed toward downstream nozzle guide vanes.

9. The combustor as recited in claim 8 , further comprising a plurality of studs which extend from said cold side of said panel.

10. The combustor as recited in claim 8 , wherein at least one of said multiple of effusion flow passages defines an angle through the panel.

11. The combustor as recited in claim 8 , wherein said wave pattern includes a multiple of transverse ridges along said multiple of peaks and troughs.

12. A method of operating a combustor section of a gas turbine engine, the method comprising:
directing an impingement flow from at least one impingement flow passage of a multiple of impingement flow passages of a shell toward at least one peak of a multiple of peaks on a cold side of a panel mounted to said shell, said panel defining a wave pattern on said cold side, said wave pattern comprising said multiple of peaks and a multiple of troughs, said multiple of troughs defining a multiple of corresponding entrances to a respective multiple of effusion passages through said panel;
directing the impingement flow from the at least one peak of said multiple of peaks toward at least one trough of said multiple of troughs;
directing the impingement flow through at least one entrance of the multiple of entrances and a respective at least one effusion passage of said multiple of effusion passages; and
wherein each of said multiple of entrances is located in a lowest portion of said multiple of troughs.

13. The method as recited in claim 12 , further comprising segregating each of the entrances.

14. The method as recited in claim 12 , further comprising separating each of the entrances from one another longitudinally by adjacent peaks and laterally by adjacent transverse ridges.

15. The method as recited in claim 12 , further comprising displacing each of the multiple of entrances from respective exits of the effusion passages such that the effusion passages define respective angles relative to a hot side of the liner panel.

Assignees

• United Technologies Corp

Inventors

• Drake Christopher

Classifications

• F23R3/002 Primary

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

• F05D2250/611

  undulated · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F23R3/005

  Combined with pressure or heat exchangers · CPC title