发明名称 |
COMBUSTOR WITH AXIAL STAGING FOR A GAS TURBINE ENGINE |
摘要 |
A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow. |
申请公布号 |
EP3008391(A1) |
申请公布日期 |
2016.04.20 |
申请号 |
EP20140811456 |
申请日期 |
2014.06.11 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
HOKE, JAMES B.;MCKINNEY, RANDAL G.;CHEUNG, ALBERT K. |
分类号 |
F23R3/42;F23R3/46 |
主分类号 |
F23R3/42 |
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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