| 摘要 |
A fuel injector for a gas turbine engine of an aircraft has an inlet fitting, a fuel nozzle, and a housing stem fluidly interconnecting and supporting the nozzle on the fitting. An internal heatshield assembly comprising an internal fuel conduit extends in a bore in the housing stem. An upper end of the fuel conduit has a rigid, fluid-tight connection with a fuel inlet passage in the fitting, while the lower end of the fuel conduit has a rigid, fluid-tight connection with the fuel nozzle. The bore closely surrounds the fuel conduit and a stagnant air gap is provided between the internal walls of the bore and the outer surface of the fuel conduit. The fuel conduit has a coiled portion to allow for thermal expansion.
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