| 摘要 |
A fuel nozzle assembly (10) for a gas turbine engine (12) is provided. The fuel nozzle assembly (10) includes a rocket unit (14) and a flow-guiding element, such as may include swirler elements, non-swirler elements, or a combination of swirler elements and non-swirler elements, with an aft end (18) in threaded engagement with a forward end (20) of the rocket unit (14). The fuel nozzle assembly (10) may include an oil tip (36) including a clocking feature with a mechanical constraint to orient the oil tip (36) at a predetermined angular orientation (42) relative to the swirler (16). The fuel nozzle assembly (10) may include one or more gas stage inlets (13, 15), one or more oil stage inlets (17, 19), and a flexible hose (26) to direct the oil to a plurality of rocket units (14). |
