Nozzle device for feeding fuel into a combustion chamber of a gas turbine assembly, and gas turbine assembly

Patent metadata

Field	Value
Publication number	US-12055294-B2
Application number	US-202318353487-A
Country	US
Kind code	B2
Filing date	Jul 17, 2023
Priority date	Jul 21, 2022
Publication date	Aug 6, 2024
Grant date	Aug 6, 2024

Abstract

A nozzle device for feeding fuel into a combustion chamber of a gas turbine assembly, includes: a nozzle main body having nozzle openings for injecting the fuel into the combustion chamber; a nozzle bracket having a fuel line for fluidic connection between a manifold fuel line and the main body, wherein at least a portion of the fuel line is aligned along, a central longitudinal axis; and a throttle element disposed downstream of the manifold fuel line for throttling the fuel flow to a pre-specified target quantity. The throttle element includes two stages which are fluidically disposed in series, each stage having a line portion aligned along a central longitudinal axis and a flow cross section. A relaxation chamber is disposed between the stages, the flow cross section of the relaxation chamber being larger than the flow cross section of the upstream stage.

First claim

The invention claimed is:

1. A nozzle device for feeding gaseous fuel into a combustion chamber of a gas turbine assembly, comprising:
a nozzle main body having nozzle openings for injecting the gaseous fuel into the combustion chamber;
a nozzle bracket including a fuel line for the fluidic connection between a manifold fuel line of a gaseous fuel manifold and the nozzle main body, wherein the fuel line at least in portions is aligned along, to be symmetrical to, a central longitudinal axis of the nozzle bracket; and
a throttle element, which is disposed downstream of the manifold fuel line, on an the upstream end of the fuel line, for throttling a fuel flow to a pre-specified target quantity,
wherein the throttle element comprises:
at least two stages which are fluidically disposed in series, wherein each of the two stages includes a line portion which is aligned along a respective line portion longitudinal axis and has a flow cross section, wherein each line portion has a single entrance and a single exit, wherein the respective line portion longitudinal axes of the respective line portions of the at least two stages are radially offset from one another, and
a relaxation chamber disposed between the at least two stages, a flow cross section of said relaxation chamber being larger than the flow cross section of the one of the two stages disposed upstream of the relaxation chamber, wherein an open space of the relaxation chamber at least partially overlaps the central longitudinal axis of the nozzle bracket.

2. The nozzle device according to claim 1 , wherein at least one of the line portions within the throttle element has a smaller flow cross section than the manifold fuel line and/or the fuel line downstream of the throttle element.

3. The nozzle device according to claim 1 , wherein the line portion has a circular flow cross section with a diameter, wherein a first stage of the at least two stages, disposed farthest upstream, has a flow cross section larger than others of the at least two stages.

4. The nozzle device according to claim 1 , wherein any of the at least two stages fluidically disposed downstream of one of the at least two stages has a same or a smaller flow cross section than the one of the at least two stages.

5. The nozzle device according to claim 1 , wherein the respective line portions are disposed to be at least in part mutually coaxial and/or coaxial with the central longitudinal axis.

6. The nozzle device according to claim 1 , wherein the line portion longitudinal axis of at least one of the at least two stages is radially offset from the central longitudinal axis downstream of the throttle element.

7. The nozzle device according to claim 6 , wherein the radial offset is disposed such that the line portion longitudinal axes are mutually offset by between 90° and 270° in a revolving direction.

8. The nozzle device according to claim 6 , wherein the radial offset is configured such that the flow cross sections of the line portions of at least two successive stages in terms of the radial position thereof and/or the position thereof in the revolving direction, have a small overlap, of at most 20% of the flow cross section, or no overlap.

9. The nozzle device according to claim 1 , wherein the line portion longitudinal axis of at least one of the at least two stages is disposed so as to be inclined at an angle in relation to the line portion longitudinal axis of another of the at least two stages and/or to the central longitudinal axis downstream of the throttle element.

10. The nozzle device according to claim 9 , wherein a plurality of line portion longitudinal axes disposed in succession are disposed to be inclined at the angle in relation to the central longitudinal axis downstream of the throttle element, wherein the respective inclinations alternate in a revolving direction.

11. The nozzle device according to claim 1 , wherein the throttle element comprises a cylindrical, monolithic, hollow body, the hollow body being fastened to or in the nozzle bracket while being sealed in a fluid-tight manner.

12. The nozzle device according to claim 1 , wherein the throttle element, comprises at least two individual elements or is formed therefrom, wherein each of the two individual elements comprises the line portion of one of the at least two stages.

13. The nozzle device according to claim 1 , and further comprising a plurality of the relaxation chambers, wherein the respective flow cross sections thereof, are of identical configuration.

14. The nozzle device according to claim 13 , wherein the respective flow cross sections of the relaxation chambers correspond to the flow cross section of the fuel line disposed downstream of the throttle element.

15. A gas turbine assembly having a turbine assembly having at least one of the nozzle device according to claim 1 .

16. The nozzle device according to claim 1 , wherein the relaxation chamber has a relaxation chamber longitudinal axis that is coaxial with the central longitudinal axis.

17. The nozzle device according to claim 16 , wherein an axial length of at least one of the line portions is smaller than a diameter of the at least one of the line portions.

18. The nozzle device according to claim 1 , wherein an axial length of at least one of the line portions is smaller than a diameter of the at least one of the line portions.

19. The nozzle device according to claim 1 , wherein the respective line portion longitudinal axes of the respective line portions of the at least two stages are parallel to one another.

20. The nozzle device according to claim 1 , wherein the line portion longitudinal axis of both of the at least two stages are radially offset from the central longitudinal axis downstream of the throttle element.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Clemen Carsten
• Gebel Gregor Christoffer

Classifications

• F02C7/222

  Fuel flow conduits, e.g. manifolds · CPC title

• F23D17/002

  gaseous or liquid fuel · CPC title

• F23R3/283 Primary

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R2900/00002

  Gas turbine combustors adapted for fuels having low heating value [LHV] · CPC title

• F23R3/28 Primary

  characterised by the fuel supply (burners F23D) · CPC title