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A method of transitioning from a first operating mode to a second operating in a gas turbine engine. An amount of fuel provided to a primary fuel injection system of the combustor apparatus is reduced. An amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus is

A method of transitioning from a first operating mode to a second operating in a gas turbine engine. An amount of fuel provided to a primary fuel injection system of the combustor apparatus is reduced. An amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus is reduced, wherein the secondary fuel/air injection system provides fuel to a secondary combustion zone downstream from a main combustion zone. A total amount of air provided to the combustor apparatus is reduced, wherein portions of the air are provided to each of the injection systems. Upon reaching operating parameters corresponding to the second operating mode, the amount of fuel provided to the primary fuel injection system is increased, the amount of fuel provided to the secondary fuel/air injection system is reduced, and the total amount of air provided to the combustor apparatus is increased.

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1. A method of operating a combustor apparatus in a turbine engine comprising: transitioning from a first operating mode to a second operating mode corresponding to a lesser load than the first operating mode, the method comprising: reducing an amount of fuel provided to a primary fuel injection sys

1. A method of operating a combustor apparatus in a turbine engine comprising: transitioning from a first operating mode to a second operating mode corresponding to a lesser load than the first operating mode, the method comprising: reducing an amount of fuel provided to a primary fuel injection system of the combustor apparatus, the primary fuel injection system providing fuel to a main combustion zone;reducing an amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus, the secondary fuel/air injection system providing fuel to a secondary combustion zone downstream from the main combustion zone;reducing a total amount of air provided to the combustor apparatus, wherein a first portion of the air is provided to the primary fuel injection system and a second portion of the air is provided to the secondary fuel/air injection system; upon reaching operating parameters corresponding to the second operating mode:increasing the amount of fuel provided to the primary fuel injection system;reducing the amount of fuel provided to the secondary fuel/air injection system to a predetermined value;increasing the total amount of air provided to the combustor apparatus;maintaining an air to fuel ratio in the combustion zone which is ideal for reducing carbon monoxide (CO) and nitrous oxides (NOx) emissions during the first operating mode, the second operating mode and the transition from the first to the second operating mode;transitioning from the second operating mode to a third operating mode corresponding to a lesser load than the second operating mode;reducing the amount of fuel provided to the primary fuel injection system during the transition from the second operating mode to the third operating mode;maintaining the amount of fuel provided to the secondary fuel/air injection system at the predetermined value during the transition from the second operating mode to the third operating mode; andcontinuously reducing the total amount of air provided to the combustor apparatus during the transition from the second operating mode to the third operating mode. 2. The method of claim 1, wherein increasing the amount of fuel provided to the primary fuel injection system comprises increasing the amount of fuel provided to the primary fuel injection system by substantially the same amount as the secondary fuel/air injection system is reduced to the predetermined value. 3. The method of claim 1, wherein reducing the amount of fuel provided to the secondary fuel/air injection system comprises reducing the amount of fuel provided to the secondary fuel/air injection system to substantially zero. 4. The method of claim 1, wherein the operating parameters corresponding to the second operating mode comprise a predetermined fuel/air ratio in the main combustion zone. 5. The method of claim 1, wherein the operating parameters corresponding to the second operating mode comprise a predetermined amount of CO emitted from the turbine engine. 6. The method of claim 5, wherein the predetermined amount of CO emitted from the turbine engine comprise CO emissions greater than about 5 ppmvd at 15% O2. 7. The method of claim 1, wherein: reducing the total amount of air provided to the combustor apparatus comprises maneuvering at least one inlet guide vane to permit less air into the turbine engine; andincreasing the total amount of air provided to the combustor apparatus comprises maneuvering at least one inlet guide vane to permit more air into the turbine engine. 8. The method of claim 1, wherein: reducing the total amount of air provided to the combustor apparatus comprises reducing the amount of air provided to a combustor shell of the combustor apparatus; andincreasing the total amount of air provided to the combustor apparatus comprises increasing the amount of air provided to the combustor shell. 9. The method of claim 1, wherein the combustor apparatus comprises a base plate, and air delivered to the main and secondary combustion zones passes through the base plate. 10. The method of claim 1, wherein air is provided to both the primary fuel injection system and the secondary fuel/air injection system during the first and second operating modes. 11. The method of claim 1, further comprising maintaining CO emissions of the turbine engine below about 10 ppmvd at 15% O2 during both the first and second operating modes. 12. A method of operating a combustor apparatus in a turbine engine comprising: transitioning from a full load operating mode to a part load operating mode, the method comprising: reducing an amount of fuel provided to a primary fuel injection system of the combustor apparatus, the primary fuel injection system providing fuel to a main combustion zone;reducing an amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus, the secondary fuel/air injection system providing fuel to a secondary combustion zone downstream from the main combustion zone;continuously reducing a total amount of air provided to the combustor apparatus during the transition from the full load operating mode to the part load operating mode, wherein a first portion of the air is provided to the primary fuel injection system and a second portion of the air is provided to the secondary fuel/air injection system, the second portion of air being distributed to the secondary combustion zone via at least one outlet of the secondary fuel/air injection system located at the secondary combustion zone;upon reaching operating parameters corresponding to the part load operating mode: increasing the amount of fuel provided to the primary fuel injection system;reducing the amount of fuel provided to the secondary fuel/air injection system to a predetermined value;increasing the total amount of air provided to the combustor apparatus;maintaining an air to fuel ratio in the combustion zone which is ideal for reducing carbon monoxide (CO) and nitrous oxides (NOx) emissions during the full load operating mode, the part load operating mode and the transition from the full load to the part load operating mode. 13. The method of claim 12, wherein increasing the amount of fuel provided to the primary fuel injection system comprises increasing the amount of fuel provided to the primary fuel injection system by substantially the same amount as the secondary fuel/air injection system is reduced to the predetermined value. 14. The method of claim 12, wherein reducing the amount of fuel provided to the secondary fuel/air injection system comprises reducing the amount of fuel provided to the secondary fuel/air injection system to substantially zero. 15. The method of claim 12, wherein the operating parameters corresponding to the part load operating mode comprise a predetermined amount of CO emitted from the turbine engine. 16. The method of claim 12, wherein: reducing the total amount of air provided to the combustor apparatus comprises maneuvering at least one inlet guide vane to permit less air into the turbine engine; andincreasing the total amount of air provided to the combustor apparatus comprises maneuvering at least one inlet guide vane to permit more air into the turbine engine. 17. The method of claim 12, wherein the combustor apparatus comprises a base plate, and air delivered to the main and secondary combustion zones passes through the base plate. 18. The method of claim 12, wherein air is provided to both the primary fuel injection system and the secondary fuel/air injection system during both the full load and the part load operating modes. 19. The method of claim 12, wherein the secondary fuel/air injection system comprises fuel/air passages extending through the main combustion zone and including fuel supply tubes providing fuel to midportions of said fuel/air passages between an inlet end and an outlet end of said fuel/air passages.