发明名称 |
Method and apparatus for cooling gas turbine engine igniter tubes |
摘要 |
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.
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申请公布号 |
US6557350(B2) |
申请公布日期 |
2003.05.06 |
申请号 |
US20010859611 |
申请日期 |
2001.05.17 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
FARMER GILBERT;KUTTER ELLA CHRISTINE;VISE STEVEN CLAYTON;STAKER JOHN ROBERT;AL-ROUB MARWAN;HARRIS TARIQ KAY |
分类号 |
F23R3/06;F23R3/28;F23R3/50;(IPC1-7):F02C7/22;F02C7/26 |
主分类号 |
F23R3/06 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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