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AssigneeGeneral Electric Company
InventorsGilbert Farmer, Ella Christine Kutter, Steven Clayton Vise, John Robert Staker, Marwan Al-Roub, Tariq Kay Harris
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A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.
A method for operating a gas turbine engine including a combustor, and a compressor, the combustor including a plurality of igniter tubes, and an outer liner and an inner liner that define a combustion chamber, the outer liner including a plurality of first openings sized to receive the igniter tubes therein, said method comprising the steps of:
A combustor for a gas turbine engine, said combustor comprising:
A gas turbine engine comprising a combustor comprising a plurality of igniter tubes, an annular outer liner, and an annular inner liner, said outer and inner liners defining a combustion chamber, said outer liner comprising a plurality of openings sized to receive each said igniter tube therein, each said igniter tube comprising a deflector extending radially outward from said igniter tube and configured to deflect airflow for impingement cooling of said outer liner.
Dependencies are inferred from the claim text.