Cooled pilot fuel lance
AssigneeSiemens Aktiengesellschaft
InventorUlf Nilsson
Life of this patent
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Abstract
A device for injecting fuel into a combustion chamber of a gas turbine is provided, having a distribution section to which a first fuel channel, a second fuel channel and an injection channel are coupled. The first fuel channel and the second fuel channel are arranged such that a) fuel is transportable by one of the first fuel channel and the second fuel channel to the distribution section, and b) a first quantity of fuel is transportable by the other one of the first fuel channel and the second fuel channel out of the distribution section. The injection channel is arranged such that a second quantity of fuel is injectable from the distribution section into the combustion chamber. The device further comprises an end cap with a protrusion having the injection channel inside, and extending inside the inner tube.
Claims11
A device for injecting fuel into a combustion chamber of a turbine, comprising
- a distribution section,
- a first fuel channel which is coupled to the distribution section,
- a second fuel channel which is coupled to the distribution section,
- an injection channel which is coupled to the distribution section,
- wherein the first fuel channel and the second fuel channel are arranged in such a way that
- a) fuel is transportable by one of the first fuel channel and the second fuel channel to the distribution section, and
- b) a first quantity of fuel is transportable by the other one of the first fuel channel and the second fuel channel out of the distribution section, and
- wherein the injection channel is arranged in such a way that a second quantity of fuel is injectable from the distribution section into the combustion chamber,
- a pressure control arrangement which is arranged for controlling a pressure of the fuel in at least one of the first fuel channel and the second channel such that the first quantity and the second quantity is controllable,
- an inner tube,
- an outer tube which surrounds the inner tube,
- wherein the inner tube and the outer tube are arranged coaxial with respect to each other, wherein a space is formed between an inner surface of the outer tube and an outer surface of the inner tube for forming the first fuel channel and the second fuel channel, and
- an end cap into which the injection channel is formed,
- wherein the end cap is mounted to an open end of the outer tube,
- wherein the end cap comprises a protrusion which extends inside the inner tube in such a way that a part of the first fuel channel is formed between an inner surface of the inner tube and an outer surface of the protrusion, and
- wherein a part of the injection channel is formed inside the protrusion.
A method for injecting fuel into a combustion chamber of a turbine, the method comprising
- transporting fuel by one of a first fuel channel and a second fuel channel to a distribution section,
- transporting a first quantity of fuel by the other one of the first fuel channel and the second fuel channel out of the distribution section,
- injecting a second quantity of fuel from the distribution section through an injection channel into the combustion chamber, and
- controlling the first quantity and the second quantity by controlling a pressure of the fuel in at least one of the first fuel channel and the second channel.
Dependencies are inferred from the claim text.