发明名称 |
FUEL NOZZLE |
摘要 |
A fuel nozzle for a combustor of a gas turbine engine includes a body defining an axial direction and a radial direction, an air passageway defined axially in the body, and a fuel passageway defined axially in the body radially outwardly from the air passageway. The fuel passageway has an outer wall including an exit lip at a downstream portion of the outer wall. The exit lip has a surface treatment including a swirl-inducing relief. A gas turbine engine and a method of inducing swirl in at least one of pressurised fuel and air exiting a fuel nozzle of a gas turbine engine are also presented. |
申请公布号 |
US2016097536(A1) |
申请公布日期 |
2016.04.07 |
申请号 |
US201414505765 |
申请日期 |
2014.10.03 |
申请人 |
PRATT & WHITNEY CANADA CORP. |
发明人 |
WANG Yen-Wen;DAVENPORT Nigel;HAWIE Eduardo |
分类号 |
F23R3/28 |
主分类号 |
F23R3/28 |
代理机构 |
|
代理人 |
|
主权项 |
1. A fuel nozzle for a combustor of a gas turbine engine, the fuel nozzle comprising:
a body defining an axial direction and a radial direction; an air passageway defined axially in the body; a fuel passageway defined axially in the body radially outwardly from the air passageway, the fuel passageway having an outer wall including an exit lip at a downstream portion of the outer wall, the exit lip having a surface treatment including a swirl-inducing relief. |
地址 |
Longueuil CA |