CANTED FUEL INJECTOR ASSEMBLY FOR A TURBINE ENGINE
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United States of America Patent
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Issued Date -
Sep 12, 2024
app pub date -
Mar 6, 2023
filing date -
Mar 6, 2023
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Abstract
An assembly is provided for a gas turbine engine. This turbine engine assembly includes a combustor and a fuel injector assembly. The combustor includes a combustion chamber that extends axially along and circumferentially about an axial centerline. The fuel injector assembly is configured to direct fuel and air into the combustion chamber. The fuel injector assembly includes a fuel injector nozzle and an air swirler structure. The fuel injector nozzle projects into and is coupled with the air swirler structure. The centerline axis of at least one of the fuel injector nozzle or the air swirler structure is angularly offset from the axial centerline by an offset angle in a circumferential direction about the axial centerline.
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