Fuel injector and aerodynamic flow device
AssigneeHamilton Sundstrand Corporation
InventorCarsten Ralf Mehring
Life of this patent
Estimating the term…
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.
Claims15
A fuel injector for a gas turbine engine comprising:
- a housing including a base that extends to a dome and providing an exterior surface surrounding an injector cavity, the exterior surface including forward and rearward surfaces opposite one another, and each of the forward and rearward surfaces providing a shape, the shapes different than one another;
- and
- a fuel nozzle disposed within the injector cavity, wherein the fuel nozzle includes a fuel passage including an outlet, the exterior surface including a fuel injection opening aligned with the outlet and an air injector opening offset from the fuel injection opening.
A fuel injector for a gas turbine engine comprising:
- a housing including a base that extends to a dome and providing an exterior surface surrounding an injector cavity, the exterior surface including forward and rearward surfaces opposite one another, and each of the forward and rearward surfaces providing a shape, the shapes different than one another, wherein the exterior surface is shaped like a tapered airfoil, tapering from the base to the dome;
- 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;
- a fuel injector extending through the liner at a base and axially between the apertures and the outlet, the fuel injector including a housing having the base which extends 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 each of the forward and rearward surfaces provide a shape, the shapes different than one another;
- a fuel nozzle disposed within the injector cavity and providing a fuel passage, and the housing providing an air passage in fluid communication with an air source;
- and
- a compressor arranged upstream from the combustor and configured to provide compressed air, the compressor different than the air source.
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;
- a fuel injector extending through the liner at a base and axially between the apertures and the outlet, the fuel injector including a housing having the base which extends 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 each of the forward and rearward surfaces providing a shape, the shapes different than one another;
- and
- a fuel nozzle disposed within the injector cavity and including a fuel passage having an outlet, the exterior surface including a fuel injection opening aligned with the outlet and an air injector opening offset from the fuel injection opening.
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 having the base which extends 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 each of the forward and rearward surfaces providing a shape, the shape different than one another, wherein the exterior surface is shaped like a tapered airfoil, tapering from the base to the dome.
Dependencies are inferred from the claim text.