Fuel injector and aerodynamic flow device
AssigneeHamilton Sundstrand Corporation
InventorCarsten Ralf Mehring
Life of this patent
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Abstract
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.
Claims18
A fuel injector for a gas turbine engine comprising:
- a housing extending from a base to a dome and providing an exterior surface surrounding an injector cavity, the exterior surface including forward and rearward surfaces opposite one another providing shapes that are different than one another;
- and
- a fuel nozzle disposed within the injector cavity.
A gas turbine engine comprising:
- a reverse flow annular combustor including a liner having opposing ends, with one end including apertures configured to receive compressed air and an outlet provided at the other end configured to connect to a turbine nozzle;
- and
- a fuel injector extending through the liner at a base and axially between the apertures and the outlet, the fuel injector including a housing extending from the base to a dome and providing an exterior surface surrounding an injector cavity, the exterior surface including forward and rearward surfaces respectively facing the apertures and the outlet and providing shapes that are different than one another.
Dependencies are inferred from the claim text.