Segmented annular combustion system
The present disclosure is directed to a segmented annular combustion system including a first panel fuel injector including a premix air plenum, a fuel plenum, and a plurality of first side premixing channels, where each first side premixing channel is in fluid communication with the premix air plenum, the fuel plenum, and a respective first side injection aperture of a plurality of first side injection apertures. A second panel fuel injector is circumferentially spaced from the first panel fuel injector and includes a premix air plenum, a fuel plenum, and a plurality of second side premixing channels where each second side premixing channel is in fluid communication with the premix air plenum, the fuel plenum, and a respective second side injection aperture of a plurality of second side injection apertures. A fuel nozzle is disposed circumferentially between the first panel fuel injection and the second panel fuel injector.
1. A combustion system segment, comprising:
a first panel fuel injector including a first side wall and a second side wall, the first side wall and the second side wall defining therebetween a premix air plenum, a fuel plenum, and a plurality of first side premixing channels, wherein each first side premixing channel of the plurality of first side premixing channels is in fluid communication with the premix air plenum, the fuel plenum, and a respective first side injection aperture of a plurality of first side injection apertures defined along the first side wall;
a second panel fuel injector circumferentially spaced from the first panel fuel injector, the second panel fuel injector including a first side wall and a second side wall, the first side wall and the second side wall defining therebetween a premix air plenum, a fuel plenum, and a plurality of second side premixing channels, wherein each second side premixing channel of the plurality of second side premixing channels is in fluid communication with the premix air plenum, the fuel plenum, and a respective second side injection aperture of a plurality of second side injection apertures defined along the second side wall; and
a fuel nozzle disposed circumferentially between the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector, the fuel nozzle sealingly engaged with each of the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector.
2. The combustion system segment as in claim 1 , wherein the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector at least partially define a primary combustion zone downstream from the fuel nozzle and upstream from the plurality of first side injection apertures and the plurality of second side injection apertures.
3. The combustion system segment as in claim 1 , further comprising an inner liner radially spaced from an outer liner, wherein the first panel fuel injector and the second panel fuel injector extend radially between the inner liner and the outer liner, and wherein the inner liner and the outer liner define radial flow boundaries therebetween.
4. The combustion system segment as in claim 1 , further comprising an end cover formed to connect to an outer casing of a gas turbine, wherein the first panel injector, the fuel nozzle, and the second panel fuel injector are fluidly coupled to the end cover.
5. The combustion system segment as in claim 1 , wherein the fuel nozzle is sealingly engaged with the first side wall of the first panel fuel injector via a first seal disposed between a first outer wall of the fuel nozzle and the first side wall of the first panel fuel injector and the fuel nozzle is sealingly engaged with the second side wall of the second panel fuel injector via a second seal disposed between a second outer wall of the fuel nozzle and the second side wall of the second panel fuel injector.
6. The combustion system segment as in claim 1 , wherein the first side injection apertures of the plurality of first side injection apertures of the first panel fuel injector are radially spaced along the first side wall, thereby defining a radial injection plane downstream from a primary combustion zone defined between the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector.
7. The combustion system segment as in claim 1 , wherein the second side injection apertures of the plurality of second side injection apertures of the second panel fuel injector are radially spaced along the second side wall, thereby defining a radial injection plane downstream from a primary combustion zone defined between the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector.
8. The combustion system segment as in claim 1 , wherein the plurality of first side injection apertures of the first panel fuel injector define a first radial injection plane downstream from a primary combustion zone defined between the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector, and wherein the plurality of second side injection apertures of the second panel fuel injector define a second radial injection plane downstream from the primary combustion zone, the first radial plane and the second radial plane being equidistant from an aft plate of the first fuel nozzle with respect to an axial centerline of the first fuel nozzle.
9. The combustion system segment as in claim 1 , wherein the plurality of first side injection apertures of the first panel fuel injector define a first radial injection plane downstream from a primary combustion zone defined between the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector, and wherein the plurality of second side injection apertures of the second panel fuel injector define a second radial injection plane downstream from the primary combustion zone, the first radial plane and the second radial plane being axially offset with respect to each other relative to an aft plate of the fuel nozzle.
10. The combustion system segment as in claim 1 , wherein the fuel nozzle comprises a forward plate, an aft plate, an outer shroud, a fuel plenum at least partially defined by the forward plate and the outer shroud, and a plurality of tubes that extend through the forward plate, the fuel plenum, and the aft plate, wherein one or more of the tubes is in fluid communication with the fuel plenum.
11. The combustion system segment as in claim 1 , wherein one or more of the first side premixing channels of the plurality of first side premixing channels of the first panel fuel injector extend axially along an inner surface of the second side wall of the first panel fuel injector.
12. The combustion system segment as in claim 1 , wherein one or more of the second side premixing channels of the plurality of second side premixing channels of the second panel fuel injector extend axially along an inner surface of the first side wall of the second panel fuel injector.
13. The combustion system segment as in claim 1 , wherein the first panel fuel injector extends downstream at a first axial distance from an aft plate of the fuel nozzle, and the second panel fuel injector extends downstream at a second axial distance from the aft plate of the fuel nozzle.
14. The combustion system segment as in claim 13 , wherein the first axial distance is greater than or less than the second axial distance.
15. The combustion system segment as in claim 1 , wherein the first panel fuel injector includes a plurality of second side premixing channels defined between the first side wall and the second side wall and a plurality of second side injection apertures defined along the second side wall, wherein each second side premixing channel is in fluid communication with the premix air plenum, the fuel plenum, and a respective second side injection aperture of the plurality of second side injection apertures.
16. The combustion system segment as in claim 1 , wherein the second panel fuel injector includes a plurality of first side premixing channels defined between the first side wall and the second side wall and a plurality of first side injection apertures defined along the first side wall, wherein each first side premixing channel is in fluid communication with the premix air plenum, the fuel plenum, and a respective first side injection aperture of the plurality of first side injection apertures.
17. A combustion system, comprising:
a plurality of panel fuel injectors arranged in an annular array about an axial centerline of the combustion system and a plurality of fuel nozzles, wherein each fuel nozzle of the plurality of fuel nozzles is disposed circumferentially between a respective adjacent pair of panel fuel injectors of the plurality of panel fuel injectors and is sealingly engaged with each panel fuel injector of the respective adjacent pair of panel fuel injectors;
wherein the plurality of fuel nozzles includes a first fuel nozzle;
wherein each adjacent pair of panel fuel injectors includes:
a first panel fuel injector having a first side wall and a second side wall, the first side wall and the second side wall defining therebetween a premix air plenum, a fuel plenum, and a plurality of first side premixing channels, wherein each first side premixing channel of the plurality of first side premixing channels is in fluid communication with the premix air plenum, the fuel plenum, and a respective first side injection aperture of a plurality of first side injection apertures defined along the first side wall; and
a second panel fuel injector circumferentially spaced from the first panel fuel injector via the first fuel nozzle, the second panel fuel injector including a first side wall and a second side wall, the first side wall and the second side wall defining therebetween a premix air plenum, a fuel plenum, and a plurality of second side premixing channels, wherein each second side premixing channel of the plurality of second side premixing channels is in fluid communication with the premix air plenum, the fuel plenum, and a respective second side injection aperture of a plurality of second side injection apertures defined along the second side wall.
18. The combustion system as in claim 17 , wherein the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector at least partially define a primary combustion zone downstream from the first fuel nozzle and upstream from the plurality of first side injection apertures and the plurality of second side injection apertures.
19. The combustion system as in claim 17 , further comprising an inner liner radially spaced from an outer liner, wherein the first panel fuel injector and the second panel fuel injector extend radially between the inner liner and the outer liner, and wherein the inner liner and the outer liner define radial flow boundaries therebetween.
20. The combustion system as in claim 19 , wherein the inner liner and the outer liner are configured to circumferentially span a subset of adjacent panel fuel injectors of the plurality of panel fuel injectors.
21. The combustion system as in claim 17 , further comprising an end cover formed to connect to an outer casing of a gas turbine, wherein the first panel injector, the first fuel nozzle, and the second panel fuel injector are fluidly coupled to the end cover.
22. The combustion system as in claim 21 , further comprising a plurality of end covers arranged circumferentially about the axial centerline of the combustion system, wherein a subset of adjacent panel fuel injectors of the plurality of fuel injectors and a subset of the plurality of fuel nozzles disposed between respective panel fuel injectors are coupled to each end cover of the plurality of end covers.
23. The combustion system as in claim 17 , wherein the first side injection apertures of the plurality of first side injection apertures of the first panel fuel injector are radially spaced along the first side wall, thereby defining a radial injection plane downstream from a primary combustion zone defined between the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector.
24. The combustion system as in claim 17 , wherein the second side injection apertures of the plurality of second side injection apertures of the second panel fuel injector are radially spaced along the second side wall, thereby defining a radial injection plane downstream from a primary combustion zone defined between the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector.
25. The combustion system as in claim 17 , wherein the plurality of first side injection apertures of the first panel fuel injector define a first radial injection plane downstream from a primary combustion zone defined between the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector, and wherein the plurality of second side injection apertures of the second panel fuel injector define a second radial injection plane downstream from the primary combustion zone, the first radial plane and the second radial plane being equidistant from an aft plate of the first fuel nozzle with respect to an axial centerline of the first fuel nozzle.
26. The combustion system as in claim 17 , wherein the plurality of first side injection apertures of the first panel fuel injector define a first radial injection plane downstream from a primary combustion zone defined between the first side wall of the first panel fuel injector and the second side wall of the second panel fuel injector, and wherein the plurality of second side injection apertures of the second panel fuel injector define a second radial injection plane downstream from the primary combustion zone, the first radial plane and the second radial plane being axially offset with respect to each other relative to an aft plate of the first fuel nozzle.
27. The combustion system as in claim 17 , wherein the first panel fuel injector extends downstream at a first axial distance from an aft plate of the first fuel nozzle and the second panel fuel injector extends downstream at a second axial distance from the aft plate of the first fuel nozzle.
28. The combustion system as in claim 27 , wherein the first axial distance is different from the second axial distance.
29. The combustion system as in claim 17 , wherein the first panel fuel injector includes a plurality of second side premixing channels defined between the first side wall and the second side wall and a plurality of second side injection apertures defined along the second side wall, and wherein each second side premixing channel is in fluid communication with the premix air plenum, the fuel plenum, and a respective second side injection aperture of the plurality of second side injection apertures.
30. The combustion system as in claim 17 , wherein the second panel fuel injector includes a plurality of first side premixing channels defined between the first side wall and the second side wall and a plurality of first side injection apertures defined along the first side wall, and wherein each first side premixing channel is in fluid communication with the premix air plenum, the fuel plenum, and a respective first side injection aperture of the plurality of first side injection apertures.
31. The combustion system as in claim 17 , wherein a first axial gap is defined between an aft end of the first panel fuel injector and a leading edge of a first stationary nozzle of a turbine.
32. The combustion system as in claim 17 , wherein a second axial gap is defined between an aft end of the second panel fuel injector and a leading edge of a second stationary nozzle of a turbine.