Pilot arrangement, nozzle device, method and gas turbine arrangement

Patent metadata

Field	Value
Publication number	US-12007118-B2
Application number	US-202318356416-A
Country	US
Kind code	B2
Filing date	Jul 21, 2023
Priority date	Aug 10, 2022
Publication date	Jun 11, 2024
Grant date	Jun 11, 2024

Abstract

A pilot arrangement for a nozzle of a gas turbine, includes a cavity extending along a longitudinal axis for conducting fuel, the narrowest flow cross section of which is larger than a flow cross section of a pilot fuel nozzle, and the pilot fuel nozzle, which adjoins the cavity downstream and includes a pilot line and a pilot fuel outlet arranged downstream of the pilot line, the narrowest flow cross section of which is smaller than that of the cavity. A compact configuration is achieved in that the cavity is arranged in a central body arranged on the longitudinal axis, a swirling element is arranged in a circumferential manner around the central body, wherein the central body and the swirling element form a swirling arrangement, and the swirling element, the central body and the pilot fuel nozzle are configured as a continuous, integral component.

First claim

The invention claimed is:

1. A pilot arrangement for use in a nozzle device of a gas turbine arrangement, comprising:
a pilot fuel nozzle,
a central body arranged on a longitudinal axis,
a cavity extending along the longitudinal axis for conducting fuel, a narrowest flow cross section of the cavity being configured to be larger than a flow cross section of the pilot fuel nozzle,
the pilot fuel nozzle adjoining the cavity in a downstream direction and comprising a pilot line and a pilot fuel outlet arranged at a downstream end of the pilot line, a narrowest flow cross section of the pilot line being configured to be smaller than that of the cavity,
the cavity being arranged in the central body,
at least one swirling element being arranged in a circumferential manner around the central body, wherein the central body and the at least one swirling element form a swirling arrangement,
the at least one swirling element, the central body and the pilot fuel nozzle being configured as a continuous, monolithic component,
a hollow chamber arranged as a heat shield in a circumferential manner around the pilot fuel nozzle, and
the hollow chamber being sealed in a flow-tight manner relative to an environment surrounding the pilot arrangement.

2. The pilot arrangement according to claim 1 , and further comprising:
at least one pilot fuel supply line configured for supplying fuel into the cavity, wherein the at least one pilot fuel supply line is guided through the at least one swirling element for conducting pilot fuel from a circumferential wall of an inner air channel radially inwards into the cavity.

3. The pilot arrangement according to claim 2 , wherein at least one chosen from the flow cross section of the pilot line and a flow cross-section of the at least one pilot fuel supply line is configured to be at least one chosen from round and rhombic.

4. The pilot arrangement according to claim 1 , wherein the hollow chamber is filled with an inert gas or evacuated.

5. The pilot arrangement according to claim 1 , and further comprising, at a downstream end of the central body, a lance which extends on the longitudinal axis and in which the pilot line extends at least for a most part, wherein the lance comprising the pilot line has an axial length such that the fuel outlet is positioned at least in a downstream third or quarter.

6. The pilot arrangement according to claim 5 , wherein the fuel outlet is positioned at least in a downstream third or quarter at least substantially at an outlet, of an inner air channel of the nozzle device.

7. The pilot arrangement according to claim 1 , wherein all walls of the pilot arrangement are aligned at an angle of no more than 45° to the longitudinal axis.

8. The pilot arrangement according to claim 1 , and further comprising an atomizer arranged within the fuel nozzle.

9. The pilot arrangement according to claim 8 , wherein the atomizer includes a central body comprising support structures and is arranged in the pilot line.

10. A nozzle device comprising the pilot arrangement according to claim 1 and comprising an inner air channel, which is arranged on a central longitudinal axis of the nozzle device and within which the pilot arrangement is arranged coaxially with the inner air channel.

11. A gas turbine arrangement comprising a combustion chamber arrangement comprising at least one of the nozzle device according to claim 10 and a turbine arrangement.

12. The pilot arrangement according to claim 1 , wherein the gas turbine arrangement is an aircraft engine.

13. The pilot arrangement according to claim 1 , wherein the hollow chamber is arranged around at least one chosen from the pilot line and the cavity.

14. A method for producing a pilot arrangement comprising:
providing a pilot arrangement for use in a nozzle device of a gas turbine arrangement, comprising:
a pilot fuel nozzle,
a central body arranged on a longitudinal axis,
a cavity extending along the longitudinal axis for conducting fuel, a narrowest flow cross section of the cavity being configured to be larger than a flow cross section of the pilot fuel nozzle,
the pilot fuel nozzle adjoining the cavity in a downstream direction and comprising a pilot line and a pilot fuel outlet arranged at a downstream end of the pilot line, a narrowest flow cross section of the pilot line being configured to be smaller than that of the cavity,

the cavity being arranged in the central body,
at least one swirling element being arranged in a circumferential manner around the central body, wherein the central body and the at least one swirling element form a swirling arrangement,
the at least one swirling element, the central body and the pilot fuel nozzle being configured as a continuous, monolithic component,
an atomizer arranged within the fuel nozzle,
manufacturing the at least one swirling element, the central body and the pilot fuel nozzle as the continuous monolithic component using an additive manufacturing method.

15. A pilot arrangement for use in a nozzle device of a gas turbine arrangement, comprising:
a pilot fuel nozzle,
a central body arranged on a longitudinal axis,
a cavity extending along the longitudinal axis for conducting fuel, a narrowest flow cross section of the cavity being configured to be larger than a flow cross section of the pilot fuel nozzle,
the pilot fuel nozzle adjoining the cavity in a downstream direction and comprising a pilot line and a pilot fuel outlet arranged at a downstream end of the pilot line, a narrowest flow cross section of the pilot line being configured to be smaller than that of the cavity,
the cavity being arranged in the central body,
at least one swirling element being arranged in a circumferential manner around the central body, wherein the central body and the at least one swirling element form a swirling arrangement,
the at least one swirling element, the central body and the pilot fuel nozzle being configured as a continuous, monolithic component:
wherein all walls of the pilot arrangement are aligned at an angle of no more than 45° to the longitudinal axis.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Clemen Carsten

Classifications

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• B33Y10/00

  Processes of additive manufacturing · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• F23R3/283

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

• F23R3/14

  by using swirl vanes · CPC title