| 摘要 |
A gas turbine engine includes a reverse flow annular combustor having a liner with opposing ends. One end includes apertures configured to receive compressed air, and an outlet is provided at the other end and is configured to connect to a turbine nozzle. A fuel injector extends through the liner at a base and axially between the apertures and the outlet. The fuel injector includes a housing extending from the base to a dome and provides an exterior surface surrounding an injector cavity. The exterior surface has forward and rearward surfaces respectively facing the apertures and the outlet and provides shapes that are different than one another to influence and improve the aerodynamic flow field of the gas mixture (i.e., air, fuel and combustion-products) within the combustor volume.
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