发明名称 |
Combustor |
摘要 |
An annular combustor for a gas turbine engine is constructed to include a sector that has a reduced airflow distribution than the remainder of the circumference by supplying a reduced airflow in a judiciously located portion of the fuel nozzles and the single stage of radially ingested combustion airflow. This single stage circumferential zoned annular combustor serves to accommodate higher fuel/air ratios.
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申请公布号 |
US5481867(A) |
申请公布日期 |
1996.01.09 |
申请号 |
US19880200479 |
申请日期 |
1988.05.31 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
DUBELL, THOMAS L.;SHADOWEN, JAMES H. |
分类号 |
F23C7/02;F23R3/04;F23R3/10;F23R3/26;F23R3/28;F23R3/50;F23R3/52;F23R3/54;(IPC1-7):F02C3/06 |
主分类号 |
F23C7/02 |
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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