Parker-Hannifin Corporation
AIRCRAFT FUEL NOZZLE

Abstract:

A fuel injector for an aircraft gas turbine engine includes a housing stem, a fuel nozzle coupled to the housing stem, and a fuel conduit extending through the housing stem and into the fuel nozzle where the fuel conduit bends to extend in a longitudinal downstream direction within the fuel nozzle. The fuel conduit is configured to transport bulk fuel flow further along the nozzle before being split downstream in the fuel circuit for final spray distribution, thereby promoting lower fuel temperatures. The fuel nozzle may minimize metal-to-metal contact between an external wall of the nozzle in thermal communication with ambient environment and an internal portion of the nozzle in thermal communication with the fuel circuit to minimize heat pick-up in the fuel. The fuel conduit may include a coiled section within a cavity of the fuel nozzle for compensating for thermal growth mismatches of the fuel injector.