System and method for combustion of non-gaseous fuels and derivatives thereof
The present disclosure relates to apparatuses and methods that are useful for one or more aspects of a power production plant. More particularly, the disclosure relates to combustor apparatuses and methods for a combustor adapted to utilize different fuel mixtures derived from gasification of a solid fuel. Combustion of the different fuel mixtures within the combustor can be facilitated by arranging elements of the combustor controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel mixtures.
1. A power production plant comprising:
a gasifier configured for receiving a solid fuel and providing a gaseous fuel;
a combustor having a combustor liner surrounded by an outer casing, the combustor liner defining a combustion chamber configured for receiving the gaseous fuel, an oxidant, and a diluent, and outputting a combustor exhaust stream, the combustion chamber defining a reaction zone and a dilution zone, the combustor liner further comprising a plurality of longitudinally-extending reinforcing rib members engaged with an outer surface of the combustor liner and extending toward the outer casing, wherein adjacent rib members and the outer surface of the combustor liner define a plurality of cooling channels along the outer surface of the combustor liner;
an injection arrangement configured to inject at least the oxidant into the combustion chamber of the combustor, the injection arrangement including:
a first stage oxidant injector engaging an end of the combustor liner, the first stage oxidant injector being arranged to introduce a first portion of at least the oxidant into the reaction zone of the combustion chamber through a swirler device, the swirler device of the first stage oxidant injector providing for mixing of the oxidant with the fuel, and producing recirculation about the reaction zone; and
a second stage oxidant injector arranged to introduce a second portion of at least the oxidant into the reaction zone, through a wall of the combustor liner defining the combustion chamber, downstream of the first stage oxidant injector and prior to the dilution zone of the combustion chamber, the second stage oxidant injector being configured to stabilize a flame produced by combustion and to provide additional mixing of the oxidant with the fuel prior to the dilution zone; and
a wall including a longitudinally extending portion, the wall positioned between the combustor liner and the outer casing, the wall adapted for separating a flow of the oxidant from the second stage oxidant injector and a flow of the diluent,
wherein the wall is effective to allow only oxidant to flow along an upstream portion of the combustor liner and allow only diluent to flow along a downstream portion of the combustor liner.
2. The power production plant of claim 1 , wherein at least a portion of an outer surface of the combustor liner is configured to receive a flow of any one or more of the fuel, the oxidant, and the diluent thereagainst prior to being received by the combustion chamber to thereby provide for cooling of the combustor liner.
3. The power production plant of claim 1 , wherein at least a portion of the outer surface of the combustor liner between adjacent reinforcing rib members of the plurality of reinforcing rib members is configured to receive the flow of any one or more of the fuel, the oxidant, and the diluent thereagainst prior to being received by the combustion chamber.
4. The power production plant of claim 1 , wherein the combustor liner comprises one or more openings defined therein and adapted for passage therethrough of the diluent into the combustion chamber.
5. The power production plant of claim 1 , wherein the combustor liner comprises a plurality of layers.
6. The power production plant of claim 5 , wherein the plurality of layers comprises a first, inner layer and a second, outer layer.
7. The power production plant of claim 6 , wherein the combustor liner is configured such that the first, inner layer engages the first stage oxidant injector and such that oxidant passes along an outer periphery of the first, inner layer for injection through the second stage oxidant injector.
8. The power production plant of claim 6 , wherein a space is defined between the first, inner layer and the second, outer layer.
9. The power production plant of claim 8 , wherein the plurality of longitudinally-extending reinforcing rib members are engaged with an outer surface of the second, outer layer of the combustor liner.
10. The power production plant of claim 9 , wherein the combustor liner is configured such that diluent may pass through the space defined between the first, inner layer and the second, outer layer, exit a downstream end of the combustor liner, and circulate outward to an outer periphery of the second, outer layer of the combustor liner for passage into one or more openings defined in the combustor liner that are adapted for passage therethrough of the diluent into the combustion chamber.
11. The power production plant of claim 10 , further comprising a sleeve member extending about an outer surface of the combustor liner and the plurality of reinforcing ribs.
12. The power production plant of claim 1 , wherein the swirler device is a swirl plate that comprises a central orifice through which a fuel nozzle extends and a plurality of oxidant vents surrounding the central orifice.
13. The power production plant of claim 12 , wherein the plurality of oxidant vents are angularly aligned so as to direct the oxidant into the combustion chamber at an angle relative to axial.
14. The power production plant of claim 13 , wherein the angle relative to axial is in the range of 20 degrees to 85 degrees.
15. The power production plant of claim 13 , wherein the plurality of oxidant vents are angularly aligned so as to provide an effective swirl number of 1 to 10.
16. The power production plant of claim 1 , comprising a fuel nozzle configured for injection of the fuel gas into the combustion chamber, the fuel nozzle comprising an end cone including a plurality of perforations for passage of the gaseous fuel therethrough.
17. The power production plant of claim 16 , wherein the plurality of perforations are aligned at a defined angle from the axial, the defined angle being 15 degrees to 80 degrees.