US 12,320,522 B2
Piloting arrangement, nozzle device, gas turbine arrangement and method
Christoffer Gregor Gebel, Ludwigsfelde (DE); and Carsten Clemen, Mittenwalde (DE)
Assigned to ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, Blankenfelde-Mahlow (DE)
Filed by Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow (DE)
Filed on Feb. 12, 2024, as Appl. No. 18/439,244.
Claims priority of application No. 10 2023 201 244.8 (DE), filed on Feb. 14, 2023.
Prior Publication US 2024/0271786 A1, Aug. 15, 2024
Int. Cl. F23R 3/18 (2006.01); F23R 3/34 (2006.01)
CPC F23R 3/18 (2013.01) [F23R 3/343 (2013.01)] 14 Claims
OG exemplary drawing
 
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.