Pilot nozzle of gas turbine combustor
AssigneeMitsubishi Heavy Industries, Ltd.
InventorsMasataka Ohta, Kuniaki Aoyama, Mitsuru Inada, Shigemi Mandai, Satoshi Tanimura, Katsunori Tanaka, Koichi Nishida
Life of this patent
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Abstract
A pilot nozzle of a gas turbine combustor comprises a first structure, provided near a main nozzle of a combustor that injects fuel oil, having a flow channel for a fuel gas and an outlet for the fuel gas. The first structure diffusion-injecting the fuel gas obliquely forward through the outlet to maintain a flame and to aid ignition of the fuel oil injected from the main nozzle. There is further provided a second structure which circulates in whirls a combustion gas generated due to the combustion of the fuel gas.
Claims10
A pilot nozzle of a gas turbine combustor comprising:
- a first structure, provided near a main nozzle of a combustor that injects fuel oil, having a flow channel for a fuel gas and an outlet for the fuel gas, the first structure diffusion-injecting the fuel gas obliquely forward through the outlet to maintain a flame and to aid ignition of the fuel oil injected from the main nozzle;
- and
- a second structure which circulates in whirls a combustion gas generated due to the combustion of the fuel gas.
A pilot nozzle of a gas turbine combustor comprising:
- a central axis;
- a flow channel for a fuel gas, the flow channel being parallel to the central axis;
- and
- an outlet for injecting the fuel gas and aiding ignition of a fuel oil injected from the main nozzle, wherein
- a portion of the flow channel in the vicinity of the outlet is bent towards the central axis.
Dependencies are inferred from the claim text.