Burner of a gas turbine

1. Burner of a gas turbine, comprising:

at least two part cone shells arranged offset with respect to one another and defining a cone shaped chamber with longitudinal tangential slots for feeding air therein;

a lance carrying a liquid fuel nozzle arranged centrally in the cone shaped chamber and configured to inject only a liquid fuel jet, the liquid fuel nozzle having a circular cross section, and wherein a portion of the internal flow path of the nozzle facing the cone shaped chamber is divergent in shape, wherein an internal diffuser angle (α) between a wall of the nozzle and a longitudinal axis of the cone shaped chamber is less than 5° and is constant along the length of the divergent portion of the nozzle, and the diverging portion of the nozzle has a diffuser length to internal nozzle diameter ratio between 2-6, and the internal nozzle diameter is a smaller diameter of the diverging portion, and wherein the cone shaped chamber has a cross section which is greater than a cross section of an exit of the liquid fuel nozzle at a location of fuel injection into the chamber, and wherein the lance terminates at an exit plane of the diverging portion of the nozzle, the liquid fuel nozzle having a first portion with a constant internal diameter, and extending in a direction of the longitudinal axis of the cone shaped chamber to a second portion downstream of the first portion, the second portion facing the cone shaped chamber and is divergent in shape, and wherein the internal diameter of the first portion is equal to an internal diameter of the second portion at an inlet of the second portion; and

wherein the liquid fuel nozzle is arranged in the cone shaped chamber such that immediately outside of the nozzle, droplets can start to separate from a generated liquid fuel jet, and the generated liquid jet is substantially cylindrical with a cross section larger than a largest inner cross section of the nozzle.

2. Burner as claimed in claim 1 , wherein the diffuser angle (α) is greater than 1.5°.

3. Burner as claimed in claim 1 , wherein the diverging portion of the nozzle has a diffuser angle (α) between 1.5-2.2°.

4. Burner as claimed in claim 1 , wherein the diverging portion of the nozzle has a diffuser angle (α) between 2-4°.

5. Burner as claimed in claim 1 , wherein the diverging portion of the nozzle has a diffuser length to nozzle diameter ratio between 3-5.

6. Burner as claimed in claim 1 , wherein the diverging portion of the nozzle has a diffuser length to nozzle diameter ratio of 4.

7. Burner of a gas turbine, comprising:

at least two part cone shells arranged offset with respect to one another and defining a cone shaped chamber with longitudinal tangential slots for feeding air therein;

a cylindrical lance carrying a liquid fuel nozzle arranged centrally in the cone shaped chamber and configured to inject only a liquid fuel jet, the liquid fuel nozzle having a circular cross section, and wherein a portion of the internal flow path of the nozzle facing the cone shaped chamber is divergent in shape, wherein an internal diffuser angle (α) between a wall of the nozzle and a longitudinal axis of the cone shaped chamber is less than 5° and is constant along the length of the divergent portion of the nozzle, and the diverging portion of the nozzle has a diffuser length to internal nozzle diameter ratio between 2-6, and the internal nozzle diameter is a smaller diameter of the diverging portion, and wherein the lance terminates at an exit plane of the diverging portion of the nozzle, the liquid fuel nozzle having a first portion with a constant internal diameter, and extending in a direction of the longitudinal axis of the cone shaped chamber to a second portion downstream of the first portion, the second portion facing the cone shaped chamber and is divergent in shape, and wherein the internal diameter of the first portion is equal to an internal diameter of the second portion at an inlet of the second portion; and

wherein the liquid fuel nozzle is arranged in the cone shaped chamber such that immediately outside of the nozzle, droplets can start to separate from the liquid fuel jet, and the generated liquid jet is substantially cylindrical with a cross section larger than a largest inner cross section of the nozzle.

8. Burner as claimed in claim 7 , wherein the cone shaped chamber has a cross section which is greater than a cross section of an exit of the liquid fuel nozzle at a location of fuel injection into the chamber.

9. Burner as claimed in claim 7 , wherein the diffuser angle (α) is greater than 1.5°.

10. Burner as claimed in claim 7 , wherein the diverging portion of the nozzle has a diffuser angle (α) between 1.5-2.2°.

11. Burner as claimed in claim 7 , wherein the diverging portion of the nozzle has a diffuser angle (α) between 2-4°.

12. Burner as claimed in claim 7 , wherein the diverging portion of the nozzle has a diffuser length to nozzle diameter ratio between 3-5.

13. Burner as claimed in claim 7 , wherein the diverging portion of the nozzle has a diffuser length to nozzle diameter ratio of 4.

14. Burner as claimed in claim 1 , wherein the liquid fuel nozzle has a continuous inner surface.

15. Burner as claimed in claim 7 , wherein the liquid fuel nozzle has a continuous inner surface.

16. A method for injecting of a liquid fuel jet that is substantially cylindrical, the method comprising:

arranging at least two part cone shells offset with respect to one another and defining a cone shaped chamber with longitudinal tangential slots for feeding air therein;

arranging a lance carrying a liquid fuel nozzle centrally in the cone shaped chamber and configured to inject only a liquid fuel jet, the liquid fuel nozzle having a circular cross section, and wherein a portion of the internal flow path of the nozzle facing the cone shaped chamber is divergent in shape, wherein an internal diffuser angle (α) between a wall of the nozzle and a longitudinal axis of the cone shaped chamber is less than 5° and is constant along the length of the divergent portion of the nozzle, and the diverging portion of the nozzle has a diffuser length to internal nozzle diameter ratio between 2-6, and the internal nozzle diameter is a smaller diameter of the diverging portion, and wherein the cone shaped chamber has a cross section which is greater than a cross section of an exit of the liquid fuel nozzle at a location of fuel injection into the chamber, and wherein the lance terminates at an exit plane of the diverging portion of the nozzle, the liquid fuel nozzle having a first portion with a constant internal diameter, and extending in a direction of the longitudinal axis of the cone shaped chamber to a second portion downstream of the first portion, the second portion facing the cone shaped chamber and is divergent in shape, and wherein the internal diameter of the first portion is equal to an internal diameter of the second portion at an inlet of the second portion; and

arranging the liquid fuel nozzle in the cone shaped chamber such that immediately outside of the nozzle, droplets can start to separate from a generated liquid fuel jet; and the generated liquid jet is substantially cylindrical with a cross section larger than a largest inner cross section of the nozzle.

17. The method as claimed in claim 16 , wherein the diffuser angle (α) is greater than 1.5°.

18. The method as claimed in claim 16 , wherein the diverging portion of the nozzle has a diffuser angle (α) between 1.5-2.2°.

19. The method as claimed in claim 16 , wherein the diverging portion of the nozzle has a diffuser angle (α) between 2-4°.

20. The method as claimed in claim 16 , wherein the diverging portion of the nozzle has a diffuser length to nozzle diameter ratio between 3-5.