초록 ▼

A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. A first and a second combustion stages are defined between the liners, each said combustion stage having a plurality of fuel injection bores distributed in a liner wall defining the respective stage. Va

A combustor for a gas turbine engine comprises an inner annular liner and an outer annular liner. A first and a second combustion stages are defined between the liners, each said combustion stage having a plurality of fuel injection bores distributed in a liner wall defining the respective stage. Valves at the fuel injection bores of one of the combustion stages, the valves each defining an air passage from an exterior to an interior of the combustion stage, the valves each having an actuatable member for adjusting a size of a respective air passage for air staging the combustor.

대표청구항 ▼

1. A combustor for a gas turbine engine comprising: an inner annular liner;an outer annular liner;a first combustion stage and a second combustion stage defined between the inner annular liner and the outer annular liner, each said combustion stage having a plurality of fuel injection bores distribu

1. A combustor for a gas turbine engine comprising: an inner annular liner;an outer annular liner;a first combustion stage and a second combustion stage defined between the inner annular liner and the outer annular liner, each said combustion stage having a plurality of fuel injection bores distributed between the inner annular liner and the outer annular liner, the first combustion stage and the second combustion stage being side-by-side in a fore portion of the combustor and curving into a common aft portion;first air passages at the fuel injection bores of one of the combustion stages for air entry from a plenum; andvalves at the fuel injection bores of the other one of the combustion stages, the valves each defining second air passage from the plenum 17 to an interior of the other one of the combustion stages, the valves each having an actuatable member for adjusting a size of a respective second air passage for air staging the combustor. 2. The combustor according to claim 1, wherein the first combustion stage and the second combustion stages extend generally radially inwardly with the second combustion stage being downstream of the first combustion stage, the valves being connected to the second combustion stage. 3. The combustor according to claim 1, wherein the fuel injection bores are provided on dome portions of the inner annular liner and the outer annular liner circumscribing the combustion stages. 4. The combustor according to claim 1, wherein the valves each have a cylinder forming said second air passage, with lateral openings in the cylinder defining an entry to said second air passage, the actuatable member of the valves being a piston axially displaced in the cylinder to adjust the size of the entry to said second air passage. 5. The combustor according to claim 4, wherein each of the pistons has a cone-like surface oriented radially inward. 6. The combustor according to claim 4, wherein the valves each comprise a second piston radially outward of the lateral openings during operation of the valves. 7. The combustor according to claim 1, wherein the valves each have a cylinder forming said second air passage, with lateral openings in the cylinder defining an entry to said air passage, the actuatable member of the valves being a valve cylinder with valve lateral openings, the valve cylinder being rotatable relative to the cylinder to align/offset the valve lateral openings with the lateral openings of the cylinder to adjust the size of the entry to said second air passage. 8. The combustor according to claim 1, wherein the valves each have a cylinder forming said second air passage, with fuel injection ports defined in a wall of the cylinder, and a channel formed about the wall of the cylinder and in fluid communication with the fuel injection ports. 9. A gas turbine engine comprising: a combustor chamber outer casing defining a plenum;a combustor within the plenum and comprising:an inner annular liner;an outer annular liner;a first combustion stage and a second combustion stage defined between the inner annular liner and the outer annular liner, each said combustion stage having a plurality of fuel injection bores distributed between the inner annular liner and the outer annular liner, the first combustion stage and the second combustion stage being side-by-side in a fore portion of the combustor and curving into a common aft portion;injectors at the fuel injection bores of the first combustion stage, the injectors each defining a first air passage from the plenum to an interior of the first combustion stage; andvalves at the fuel injection bores of the second combustion stage, the valves each defining a second air passage from the plenum to an interior of the second combustion stage, the valves each having an actuatable member for adjusting a size of a respective air passage for air staging the combustor; anda diffuser having outlets communicating with the plenum. 10. The gas turbine engine according to claim 9, wherein the first combustion stage and the second combustion stage extend generally radially inwardly with the second combustion stage being downstream of the first stage. 11. The gas turbine engine according to claim 9, wherein the fuel injection bores are provided on dome portions of the inner annular liner and the outer annular liner circumscribing the combustion stages. 12. The gas turbine engine according to claim 9, wherein the valves each have a cylinder forming said second air passage, with lateral openings in the cylinder defining an entry to said second air passage, the actuatable member of the valves being a piston axially displaced in the cylinder to adjust the size of the entry to said air passage. 13. The gas turbine engine according to claim 12, wherein each of the pistons has a cone-like surface oriented radially inward. 14. The gas turbine engine according to claim 13, wherein the valves each comprise a second piston radially outward of the lateral openings during operation of the valves. 15. The gas turbine engine according to claim 9, wherein the valves each have a cylinder forming said second air passage, with lateral openings in the cylinder defining an entry to said second air passage, the actuatable member of the valves being a valve cylinder with valve lateral openings, the valve cylinder being rotatable relative to the cylinder to align/offset the valve lateral openings with the lateral openings of the cylinder to adjust the size of the entry to said second air passage. 16. The gas turbine engine according to claim 9, wherein the valves each have a cylinder forming said second air passage, with fuel injection ports defined in a wall of the cylinder, and a channel formed about the wall of the cylinder and in fluid communication with the fuel injection ports. 17. The gas turbine engine according to claim 9, wherein the valves each have a shaft projecting through a wall of the combustor chamber outer case, with an actuator of each said valve positioned outside of the combustor chamber outer casing. 18. The gas turbine engine according to claim 17, wherein the second combustion stage has a dome wall extending radially beyond the first combustion stage and relatively closer to the combustor chamber outer casing.