Gas turbine engine wave geometry combustor liner panel
AssigneeUnited Technologies Corporation
InventorChristopher Drake
Life of this patent
Estimating the term…
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.
Claims20
A panel for a combustor of a gas turbine engine, the panel comprising:
- a cold side defining at least one convex portion and at least one concave portion in communication with a passage.
A combustor of a gas turbine engine, the combustor comprising:
- a shell with 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.
A method of operating a combustor section of a gas turbine engine, the method comprising:
- 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.
Dependencies are inferred from the claim text.