Piloting arrangement, nozzle device, gas turbine arrangement and method

Patent metadata

Field	Value
Publication number	US-12320522-B2
Application number	US-202418439244-A
Country	US
Kind code	B2
Filing date	Feb 12, 2024
Priority date	Feb 14, 2023
Publication date	Jun 3, 2025
Grant date	Jun 3, 2025

Abstract

A pilot arrangement for a nozzle of a gas turbine, in particular of an aircraft engine, including: a cavity extending along a longitudinal axis for conducting fuel, a narrowest flow cross section of which is larger than a flow cross section of a pilot fuel nozzle, in particular a pilot line. The pilot fuel nozzle, which adjoins the cavity in a downstream direction includes the pilot line and a pilot fuel outlet arranged at the downstream end of the pilot line, the narrowest flow cross section of which is configured to be smaller than that of the cavity. Reliable operation is made possible by virtue of an air opening arranged on the pilot arrangement in flow connection with the cavity so there can be an at least occasional flow of air through at least the cavity and the pilot fuel nozzle during the operation of the gas turbine.

First claim

The invention claimed is:

1. A method for operating a gas turbine arrangement, comprising:
providing a gas turbine arrangement comprising a combustion chamber arrangement comprising at least one nozzle device and a turbine arrangement;
the at least one nozzle device comprising a pilot arrangement and an inner air channel, the inner air channel being arranged on a central longitudinal axis of the at least one nozzle device, the pilot arrangement being arranged within the inner air channel coaxially with the inner air channel;
the pilot arrangement comprising:
a pilot fuel nozzle;
a cavity extending along a 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 having a pilot line and a pilot fuel outlet arranged at a downstream end of the pilot line, the pilot line having a narrowest flow cross section which is configured to be smaller than the narrowest flow cross section of the cavity;
an air opening arranged on the pilot arrangement in flow connection with the cavity such that there is an at least occasional flow of air through at least the cavity and the pilot fuel nozzle during operation of the gas turbine arrangement;

wherein the cavity is arranged in a central body arranged on the longitudinal axis, and at least one swirling element is arranged circumferentially around the central body, wherein the central body and the at least one swirling element form a swirling arrangement;
at least one pilot fuel supply line for supplying fuel into the cavity, wherein the at least one pilot fuel supply line is guided through the at least one swirling element to conduct pilot fuel from a circumferential wall of the inner air channel radially inwards into the cavity;
providing an at least occasional flow of air through at least the cavity and the pilot fuel nozzle,
flowing fuel through the pilot arrangement, while not flowing air and/or fuel through the air opening in flow contact with the cavity and the pilot fuel nozzle, and,
providing that, when the pilot arrangement is deactivated, there is the at least occasional throughflow of air in a direction of the pilot fuel nozzle.

2. A pilot arrangement for use in a nozzle device of a gas turbine arrangement, comprising:
a pilot fuel nozzle;
a cavity extending along a 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 having a pilot line and a pilot fuel outlet arranged at a downstream end of the pilot line, the pilot line having a narrowest flow cross section which is configured to be smaller than the narrowest flow cross section of the cavity;
an air opening arranged on the pilot arrangement in flow connection with the cavity such that, when installed in the nozzle device of the gas turbine arrangement, there is an at least occasional flow of air through at least the cavity and the pilot fuel nozzle during operation of the gas turbine arrangement;
wherein the cavity is arranged in a central body arranged on the longitudinal axis, and at least one swirling element is arranged circumferentially around the central body, wherein the central body and the at least one swirling element form a swirling arrangement;
at least one pilot fuel supply line for supplying fuel into the cavity, wherein the at least one pilot fuel supply line is guided through the at least one swirling element to conduct 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 the at least one swirling element, the central body and the pilot fuel nozzle are configured as a continuous, integral component.

4. The pilot arrangement according to claim 2 , wherein the air opening is arranged on a side of the pilot arrangement which faces upstream in relation to an air inflow direction in direct flow contact with the cavity or in direct flow contact with the at least one pilot fuel supply line on the at least one swirling element.

5. The pilot arrangement according to claim 2 , wherein the air opening is configured to generate a pressure loss during operation such that, when there is a fuel flow through the pilot arrangement, there is no flow of air through the air opening and, after the fuel flow has been switched off, there is an at least occasional flow of air through the air opening.

6. The pilot arrangement according to claim 2 ,
wherein the air opening includes at least one orifice opening and/or a porous structure.

7. The pilot arrangement according to claim 2 ,
wherein the air opening is configured as a throttle element formed integrally with the pilot arrangement or as a separate throttle element attached to the pilot.

8. The pilot arrangement according to claim 2 , and further comprising a hollow chamber arranged as a heat shield circumferentially around the pilot fuel nozzle and/or the cavity, wherein the hollow chamber is sealed in a flow-tight manner relative to an external environment.

9. The pilot arrangement according to claim 8 , wherein the hollow chamber is arranged circumferentially around the pilot line.

10. The pilot arrangement according to claim 9 , wherein the hollow chamber is filled with an inert gas or evacuated.

11. The pilot arrangement according to claim 2 ,
wherein at the downstream end of the central body, a lance is provided which extends on the longitudinal axis and in which the pilot line extends, wherein the lance comprising the pilot line has an axial length such that the pilot fuel outlet is positioned at least in a downstream third or quarter of an inner air channel of the nozzle device when the pilot arrangement is installed in the nozzle device.

12. The pilot arrangement according to claim 11 , wherein the pilot fuel outlet is positioned at least substantially at an outlet of the inner air channel of the at least one nozzle device.

13. A nozzle device comprising the pilot arrangement according to claim 2 and comprising an inner air channel, the inner air channel arranged on a central longitudinal axis of the nozzle device and within which the pilot arrangement is arranged coaxially with the inner air channel.

14. A gas turbine arrangement comprising a combustion chamber arrangement comprising at least one of the nozzle device according to claim 13 and a turbine arrangement.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Gebel Christoffer Gregor
• Clemen Carsten

Classifications

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23R3/04

  Air inlet arrangements · CPC title

• F23R3/18 Primary

  Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants · CPC title