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US 6,655,149 B2Granted
Preferential multihole combustor liner
AssigneeGeneral Electric Company
InventorsGilbert Farmer, Daniel Dale Brown, Myron Edward Rutherford
Life of this patent
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Abstract
A multi-hole cooled combustor liner is provided which reduces hot streaks and associated material distress in the liner. Areas of increased cooling hole density are disposed upstream of the primary dilution holes and in circumferential alignment with fuel cup centers. Additional cooling holes are provided in between primary dilution holes are arranged in alternating pairs of circumferentially angled holes so as to provide a converging cooling air flow in the downstream direction.
Claims11
A gas turbine combustor liner comprising:
- a shell having forward and aft ends and defining a longitudinal axis;
- at least one dilution hole formed in said shell;
- and
- a first group of cooling holes formed in said shell, said group comprising first and second sub-groups, wherein said first sub-group of cooling holes is disposed in line with said dilution hole in a circumferential direction and on a first circumferential side of said dilution hole, and wherein said cooling holes of said first sub-group are angled with respect to said longitudinal axis in a first circumferential direction towards said dilution hole;
- and wherein said second sub-group of cooling holes is disposed in line with said dilution hole in a circumferential direction and on a second circumferential side of said dilution hole, and wherein said cooling holes of said second sub-group are angled with respect to said longitudinal axis in a second circumferential direction, opposite to said first circumferential direction.
2 more elements
Dependencies are inferred from the claim text.