Low emission gas turbine combustor
An annular combustor for a gas turbine has a combustion chamber having an interior volume that, in longitudinal section, includes a forward volume, an intermediate volume and an aft volume. The forward volume represents from about 30% to about 40% of the combustor interior volume, the intermediate volume represents from about 10% to about 20% of the combustor interior volume, and the aft volume represents from about 40% to about 60% of the combustor interior volume.
1. An annular combustor for a gas turbine engine, comprising:
an inboard liner extending longitudinally fore to aft, the inboard liner having a forward section and an aft section;
an outboard liner spaced radially outboard of and circumscribing the inboard liner, the outboard liner having a forward section and an aft section;
a bulkhead extending between a forward end of the inboard liner and a forward end of the outboard liner and cooperating therewith to define a combustion interior volume extending fore to aft from the bulkhead to an annular combustor exit boundary extending between an aft end of the inboard liner and an aft end of the outboard liner;
a plurality of combustion air admission holes formed in the inboard liner, each air admission hole having a center, the plurality of combustion air admission holes arranged with the respective centers of the plurality of combustion air admission holes disposed in a circumferential row; and
a plurality of combustion air admission holes formed in the outboard liner, each aid admission hole having a center, the plurality of combustion air admission holes arranged with the respective centers of the plurality of combustion air admission holes disposed in a circumferential row;
wherein, in longitudinal section, the combustor interior volume includes a forward volume extending fore to aft from the bulkhead to a first annular boundary extending between an aft end of the forward section of the inboard liner and an aft end of the forward section of the outboard liner, and aft volume extending fore to aft from a second annular boundary extending between the centers of the row of combustion air admission holes in the inboard liner and the centers of the row of combustion air admission holes in the outboard liner and the annular combustor exit boundary; and an intermediate volume extending fore to aft from a forward end interfacing with an aft end of the forward volume to an aft end interfacing with a forward end of the aft volume; the forward volume representing from about 30% to about 40% of the combustor interior volume; the intermediate volume representing from about 10% to about 20% of the combustor interior volume; and the aft volume representing from about 40% to about 60% of the combustor interior volume.
2. The annular combustor as recited in claim 1 wherein: the forward volume represents about 35% of the combustor interior volume; the intermediate volume represents about 20% of the combustor interior volume; and the aft volume represents about 45% of the combustor interior volume.
3. The annular combustor as recited in claim 1 wherein the forward section of the inboard liner and the forward section of the outboard liner converge from fore to aft.
4. The annular combustor as recited in claim 3 wherein:
the forward section of the inboard liner converges toward the forward section of the outboard liner at an included interior angle in the range of from 70 degrees to 85 degrees; and
the forward section of the outboard liner converges toward the forward section of the inboard liner at an included interior angle in the range of from 70 degrees to 85 degrees.
5. The annular combustor as recited in claim 4 wherein:
the forward section of the inboard liner converges toward the forward section of the outboard liner at an included interior angle in the range of from 74 degrees to 78 degrees.
6. The annular combustor as recited in claim 4 wherein:
the forward section of the outboard liner converges toward the forward section of the inboard liner at an included interior angle in the range of from 74 degrees to 78 degrees.
7. The annular combustor as recited in claim 3 wherein:
the aft section of the inboard liner extends aftwardly from the aft end of the forward section of the inboard liner at an angle in the range of from 180 degrees to 200 degrees; and
the aft section of the outboard liner extends aftwardly from the aft end of the forward section of the outboard liner at an angle in the range of from 180 degrees to 200 degrees.
8. The annular combustor as recited in claim 7 wherein:
the aft section of the inboard liner at an angle in the range of from 188 degrees to 192 degrees.
9. The annular combustor as recited in claim 7 wherein:
the aft section of the outboard liner extends aftwardly from the aft end of the forward section of the outboard liner at an angle in the range of from 190 degrees to 196 degrees.
10. The annular combustor as recited in claim 1 further comprising a plurality of fuel injectors mounted in the bulkhead, the fuel injectors disposed in a circumferential array at equally spaced circumferential intervals, S, wherein a ratio S/D has a value in the range of at least 1.1 to not greater than 1.30, D being the annular depth in a radial direction of the combustor interior volume between the inboard liner and the outboard liner at the interface of the intermediate volume with the aft volume.
11. The annular combustor as recited in claim 10 wherein the ratio S/D has a value in the range of 1.25 to 1.30.
12. The annular combustor as recited in claim 10 wherein the ratio S/H has a value in the range of at least 0.9 to less than 0.95, H being the annular height in a radial direction of the bulkhead extending between the forward end of the inboard liner and the forward end of the outboard liner.
13. The annular combustor as recited in claim 1 wherein the gas turbine engine comprises an aircraft gas turbine engine.
14. The annular combustor as recited in claim 1 wherein the gas turbine engine comprises an industrial gas turbine engine.
15. The annular combustor as recited in claim 1 wherein each of the inboard and the outboard liners comprise double-wall liners.
16. The annular combustor of claim 1 wherein each of the inboard and the outboard liners comprise single-wall liners.
17. A gas turbine combustor having a combustor interior volume comprising;
an inboard liner extending longitudinally fore to aft, the inboard liner having a forward section and an aft section, the aft section of the inboard liner extending aftwardly from the aft end of the forward section of the inboard liner at an angle in the range of from 180 degrees to 200 degrees; and
an outboard liner spaced radially outboard of and circumscribing the inboard liner, the outboard liner having a forward section and an aft section, the aft section of the outboard liner extending aftwardly from the aft end of the forward section of the outboard liner at an angle in the range of from 180 degrees to 200 degrees;
wherein, in longitudinal section, the forward section of the inboard liner converges toward the forward section of the outboard liner at an included interior angle in the range of from 70 degrees to 85 degrees, and the forward section of the outboard liner converges toward the forward section of the inboard liner at an included interior angle in the range of from 70 degrees to 85 degrees, the forward section of the inboard liner and the forward section of the outboard liner bounding a forward volume representing from about 30% to about 40% of the combustor volume.
18. A gas turbine engine combustor as recited in claim 17 further comprising:
a plurality of combustion air admission holes formed in the aft section of the inboard liner and arranged in a circumferentially extending row; and
a plurality of combustion air admission holes formed in the aft section of the outboard liner and arranged in a circumferentially extending row;
a forward portion of the aft section of the inboard liner and a forward portion of the aft section of the outboard liner bounding an intermediate volume representing from about 10% to about 20% of the combustor interior volume, and
an aft portion of the aft section of the inboard liner and an aft portion of the aft section of the outboard liner bounding an aft volume representing from about 40% to about 60% of the combustor interior volume, wherein the forward portions of the respective aft sections of the inboard and outboard liners lie upstream of the respective rows of combustion air admission holes in the inboard and outboard liners, and the aft portions of the respective aft sections of the inboard and outboard liners lie downstream of the respective rows of combustion air admission holes in the inboard and outboard liners.
19. A gas Turbine engine combustor as recited in claim 17 wherein, in longitudinal section, the forward section of the inboard liner converges toward the forward section of the outboard liner at an included interior angle in the range of from 74 degrees to 78 degrees, and the forward section of the outboard liner converges toward the forward section of the inboard liner at an included interior angle in the range of from 74 degrees to 78 degrees, the forward section of the inboard liner and the forward section of the outboard liner bounding a forward volume representing from about 35% of the combustor volume.
20. A gas turbine combustor as recited in claim 19 wherein:
the forward portion of the aft section of the inboard liner and the forward portion of the aft section of the outboard liner bounding an intermediate volume representing from about 20% of the combustor interior volume, and
the aft portion of the aft section of the inboard liner and the aft portion of the aft section of the outboard liner bounding an aft volume representing from about 45% of the combustor interior volume.
21. A gas turbine combustor having a combustor interior volume comprising;
an inboard liner extending longitudinally fore to aft, the inboard liner having a forward section and an aft section, the inboard liner including a plurality of combustion air admission holes formed in the aft section of the inboard liner and arranged in a circumferentially extending row;
an outboard liner space radially outboard of and circumscribing the inboard liner, the outboard liner spaced radially outboard of and circumscribing the inboard liner, the outboard liner having a forward section and an aft section, the outboard liner including a plurality of combustion air admission holes formed in the aft section of the outboard liner and arranged in a circumferentially extending row;
a bulkhead extending between a forward end of the inboard liner and a forward end of the outboard liner; and
a plurality of fuel injectors mounted in the bulkhead, the fuel injectors disposed in a circumferential array at equally spaced circumferential intervals, S, wherein a ratio S/D has a value in the range of at least 1.1 to not greater than 1.30, D being an annular depth in a radial direction along an annular boundary extending between the circumferential row of combustion air admission holes in the aft section of the inboard liner and the circumferential row of combustion air admission holes in the aft section of the outboard liner.
22. The gas turbine combustor as recited in claim 21 wherein the ratio S/D has a value in the range of 1.25 to 1.30.
23. The annular combustor as recited in claim 21 wherein the ratio S/H has a value in the range of at least 0.9 to less than 0.95, H being an annular height in a radial direction of the bulkhead extending between the forward end of the inboard inner and the forward end of the outboard liner.