Fuel nozzle assembly with removable components

Abstract

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 ).

1 . A fuel nozzle assembly of a gas turbine engine, comprising:
 a flow-guiding element; and   an oil tip including a clocking feature with a mechanical constraint to orient the oil tip at a predetermined angular orientation relative to the flow-guiding element.   
     
     
         2 . The fuel nozzle assembly of  claim 1 , further comprising a rocket unit and an aft end of the flow-guiding element in threaded engagement with a forward end of the rocket unit. 
     
     
         3 . The fuel nozzle assembly of  claim 2 , further comprising an aft end of an oil tube of the rocket unit threadably engaged to a flexible hose to the rocket unit. 
     
     
         4 . The fuel nozzle assembly of  claim 1 , wherein said clocking feature includes:
 a plurality of lobes separated by an angular interval around a circumference of a forward end of the flow-guiding element; and   a radial projection at an aft end of the oil tip, said radial projection selectively received within one of the lobes to orient the oil tip at the predetermined angular orientation.   
     
     
         5 . The fuel nozzle assembly of  claim 1 , further comprising a seal positioned between an annular surface of a forward end of the flow-guiding element and a surface of an aft end of the oil tip, wherein the seal is compressed by a predetermined amount based on contact between the surface and a step of the flow-guiding element positioned outside and forward of the annular surface. 
     
     
         6 . The fuel nozzle assembly of  claim 5 , further including a nut with a central opening to secure the oil tip;
 wherein the nut includes internal threads in threaded engagement with external threads on the forward end of the flow-guiding element to initiate the contact between the surface and the step.   
     
     
         7 . The fuel nozzle assembly of  claim 6 , wherein a forward end of the nut includes a plurality of fingers separated by axial slots such that the fingers are radially adjustable to engage an annular ramp at the aft end of the oil tip. 
     
     
         8 . The fuel nozzle assembly of  claim 1 , wherein the flow-guiding element comprises a non-swirler element. 
     
     
         9 . The fuel nozzle assembly of  claim 1 , wherein the flow-guiding element comprises a swirler element. 
     
     
         10 . The fuel nozzle assembly of  claim 1 , wherein the flow-guiding element comprises a combination of at least one non-swirler element and at least one swirler element.