Fuel injector having tip cooling
According to various embodiments, a system includes a gasification fuel injector. The gasification fuel injector includes a tip portion, an annular coolant chamber disposed in the tip portion, a recessed surface for cooling control and a first structural support extending through the annular coolant chamber. The first structural support divides the annular coolant chamber into a first passage and a second passage.
1. A system, comprising:
a gasification fuel injector, comprising:
a fuel passage configured to inject a fuel;
a first oxygen passage configured to inject oxygen;
a tip portion disposed about a central axis, the fuel passage, and the first oxygen passage, wherein the tip portion is disposed downstream from an upstream side of the gasification fuel injector relative to flows of the fuel and the oxygen through the fuel passage and the first oxygen passage, respectively;
a coolant chamber disposed in the tip portion; and
a curved recess disposed downstream of the coolant chamber along an exterior surface of the tip portion adjacent an outlet of the gasification fuel injector, wherein the curved recess has a curved cross-section disposed circumferentially around the central axis and a first portion of the exterior surface of the tip portion, a second portion of the exterior surface of the tip portion is disposed circumferentially around the central axis and the curved recess, and the curved cross-section of the curved recess is recessed relative to both the first and second portions of the exterior surface in an axial upstream direction relative to the central axis.
2. The system of claim 1 , comprising a gasifier having the gasification fuel injector.
3. The system of claim 1 , wherein the curved cross-section comprises a U-shape disposed circumferentially around the central axis and the first portion of the exterior surface of the tip portion, and the U-shape of the curved recess is recessed relative to both the first and second portions of the exterior surface in the axial upstream direction relative to the central axis.
4. The system of claim 1 , comprising a sacrificial material disposed in the curved recess.
5. The system of claim 4 , wherein the sacrificial material comprises a plurality of sacrificial layers.
6. The system of claim 1 , wherein the curved recess is configured to offset a maximum thermal stress point of a thermal stress distribution from a maximum mechanical stress point of a mechanical stress distribution in the tip portion.
7. The system of claim 1 , wherein the tip portion comprises a wall between the curved recess and the coolant chamber, and wherein the wall decreases in thickness from a maximum thermal stress point to a maximum mechanical stress point in the tip portion.
8. The system of claim 1 , comprising a second oxygen passage and a coolant supply pipe, wherein the coolant supply pipe coaxially surrounds the second oxygen passage.
9. The system of claim 1 , wherein the curved cross-section of the curved recess comprises first and second side walls that radially oppose one another relative to the central axis, the first and second side walls of the curved cross-section extend circumferentially around the central axis and the first portion of the exterior surface of the tip portion, the first side wall is recessed relative to the first portion of the exterior surface in the axial upstream direction relative to the central axis, and the second side wall is recessed relative to the second portion of the exterior surface in the axial upstream direction relative to the central axis.
10. The system of claim 1 , comprising a plurality of structures extending across the curved recess.
11. The system of claim 1 , wherein the curved cross-section has a wavy curvature between the first and second portions of the exterior surface of the tip portion.
12. The system of claim 1 , wherein the tip portion comprises a first wall thickness between the curved recess and the coolant chamber and a second wall thickness between the curved recess and the outlet, wherein the first wall thickness is greater than the second wall thickness.
13. The system of claim 1 , wherein the tip portion comprises a first wall thickness between the curved recess and the coolant chamber and a second wall thickness between the curved recess and the outlet, wherein the first wall thickness is lesser than the second wall thickness.
14. The system of claim 1 , wherein the tip portion comprises a first wall thickness between the curved recess and the coolant chamber and a second wall thickness between the curved recess and the outlet, wherein the first wall thickness is substantially equal to the second wall thickness.
15. The system of claim 1 , wherein the curved recess comprises a substantially annular curved recess.
16. The system of claim 1 , wherein the curved cross-section of the curved recess is recessed in the axial upstream direction to a first depth relative to the first portion of the exterior surface and a second depth relative to the second portion of the exterior surface.
17. The system of claim 1 , wherein the fuel passage and the first oxygen passage are coaxial or concentric with one another.
18. The system of claim 1 , wherein the first oxygen passage is configured to inject the oxygen as a pure oxygen, an oxygen mixture, or air.