- 专利标题: Pilot nozzle of gas turbine combustor
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申请号: US10200165申请日: 2002-07-23
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公开(公告)号: US06668557B2公开(公告)日: 2003-12-30
- 发明人: Masataka Ohta , Kuniaki Aoyama , Mitsuru Inada , Shigemi Mandai , Satoshi Tanimura , Katsunori Tanaka , Koichi Nishida
- 申请人: Masataka Ohta , Kuniaki Aoyama , Mitsuru Inada , Shigemi Mandai , Satoshi Tanimura , Katsunori Tanaka , Koichi Nishida
- 优先权: JP2001-223208 20010724
- 主分类号: F02C7264
- IPC分类号: F02C7264
摘要:
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.
公开/授权文献
- US20030019213A1 Pilot nozzle of gas turbine combustor 公开/授权日:2003-01-30