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1. 发明专利

JP2016003852A マルチ燃料対応のガスタービン燃焼器审中-公开
公开(公告)号：JP2016003852A
公开(公告)日：2016-01-12
申请号：JP2015026716
申请日：2015-02-13
申请人： KAWASAKI HEAVY IND LTD
发明人： OGATA MASAHIRO , ODA TAKEO , KINOSHITA YASUHIRO
IPC分类号： F23R3/36 , F02C7/22 , F02C9/40 , F23R3/18 , F23R3/30 , F23R3/34
摘要：【課題】メインバーナで予混合燃焼による良好な低エミッション性能を維持し、かつ追焚きバーナで水素ガスを低NOxで燃焼させるマルチ燃料対応のガスタービン燃焼器を提供する。【解決手段】燃焼室10内の第1燃焼領域S1に第1燃料F1を含む予混合気Mを供給して燃焼させるメインバーナ12と、燃焼室10内の第1燃焼領域S1よりも下流の第2燃焼領域S2に、第1燃料F1とは異なる組成の第2燃料F2を供給して燃焼させる追焚きバーナ20とを備える。第1燃料F1は炭化水素系であり、第2燃料F2は水素の安定燃焼限界濃度を超える濃度で水素を含有するガスである。【選択図】図2

2. 发明专利

JP2011226651A Gas turbine control device 有权
标题翻译：气体涡轮控制装置
公开(公告)号：JP2011226651A
公开(公告)日：2011-11-10
申请号：JP2010093667
申请日：2010-04-15
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： KUROSAKA SATOSHI , ASHIKAGA MITSUGI , OGATA MASAHIRO , HOSOKAWA YASUSHI , NISHI MUNEYUKI , SATO TAKESHI
IPC分类号： F23R3/40 , F02C9/00 , F02C9/28
CPC分类号： F23N1/042 , F02C3/205 , F02C9/28 , F23C13/02 , F23N5/022 , F23N2023/54 , F23N2037/12 , F23N2037/20 , F23N2041/20 , F23R3/40
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine control device capable of maintaining stable combustion and favorable gas-exhaust performance even when a catalyst degrades.SOLUTION: A gas turbine control device 6 includes a combustion device 2 that premixes compressed air CA from a compressor 1 with a main fuel MF and burns the mixed gas by using a catalyst to supply it to a turbine 3. The combustion device 2 is the gas turbine control device 6 having a catalyst combustion unit 21 carrying the catalyst and a preburner 7 that supplies the compressed air CA with a preheating fuel PF at an upper stream side to burn it. There are provided a storage means 6c that stores a difference between an inlet temperature t1 and an outlet temperature t2 of the newly used catalyst combustion unit 21 as an initial value D and a preburner fuel combustion control means 6a that controls a fuel supply amount to the preburner 7 on the basis of an aging difference Δd between a difference d between the inlet temperature and the outlet temperature of the catalyst combustion unit 21 and the initial value D.
摘要翻译：要解决的问题：提供即使在催化剂劣化的情况下也能够保持燃烧稳定和气体排气性能良好的燃气轮机控制装置。解决方案：燃气轮机控制装置6包括燃烧装置2，其将来自压缩机1的压缩空气CA与主燃料MF预混合，并通过使用催化剂燃烧混合气体以将其供应到涡轮机3。图2是具有承载催化剂的催化剂燃烧单元21的燃气轮机控制装置6和在上游侧向压缩空气CA供给预热燃料PF以进行燃烧的预燃器7。设置有存储装置6c，其存储新使用的催化剂燃烧单元21的入口温度t1和出口温度t2之间的差作为初始值D，以及控制燃料供给量的预燃烧器燃料燃烧控制装置6a 基于催化剂燃烧单元21的入口温度和出口温度之间的差d与初始值D之间的老化差Δd的预燃室7。（C）2012，JPO＆INPIT

3. 发明专利

JP2004324618A Gas turbine engine with intake air flow rate controller 审中-公开
公开(公告)号：JP2004324618A
公开(公告)日：2004-11-18
申请号：JP2003124008
申请日：2003-04-28
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： HOSOKAWA YASUSHI , AIDA MAKOTO , OGATA MASAHIRO
IPC分类号： F02C7/057 , F02C9/16 , F23R3/30 , F23R3/40
CPC分类号： F02C7/057 , F02C9/50 , F05D2270/08 , F23R3/26
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine engine capable of stably controlling the air flow rate so that the air-fuel ratio in the combustor remains within a proper range suitable for controlling the discharge of air pollutants according to the load of the engine.
SOLUTION: The gas turbine engine comprising a compressor 1, a combustor 2 and a turbine 3 further comprises an air flow rate controlling valve 7 on an intake air channel 80 for supplying air A to the compressor 1; and an air flow rate controlling means 6B for controlling the intake air flow rate by way of the flow rate controlling valve 7, so that the air-fuel ratio in the combustor 2 remains within a proper range suitable for controlling the discharge of the air pollutants according to the load of the engine.
COPYRIGHT: (C)2005,JPO&NCIPI

4. 发明专利

JPH08233271A BURNER OF COMBUSTOR 失效
公开(公告)号：JPH08233271A
公开(公告)日：1996-09-10
申请号：JP6182495
申请日：1995-02-23
申请人： KAWASAKI HEAVY IND LTD
发明人： KAJITA SHINICHI , OGA SHINICHI , OGATA MASAHIRO , KITAJIMA JUNICHI , KIMURA TAKEKIYO
IPC分类号： F23R3/14 , F23D14/02 , F23R3/28
摘要： PURPOSE: To obtain a burner of a combustor of which the fore end part can be cooled sufficiently, in regard to a premix combustion type burner used mainly for a multiburner combustor. CONSTITUTION: A fore end part 36 of fuel introducing pipes 32 and 33 is inserted into and disposed in a combustion chamber. An air introducing passage 42 is provided in the outer periphery of the fuel introducing pipes 32 and 33 and fuel nozzles 34 jetting fuel into the air introducing passage 42 are provided. After the fuel passes through the fore end part 36 of the fuel introducing pipes 32 and 33, it is turned back to the base end side of these pipes by a fuel introducing passage 35 and introduced into the fuel nozzles 34. The fuel supplied is made to run against the inside of the fore end part 36 so that it be subjected to impingement cooling.

5. 发明专利

JP2005241178A Combustion device of gas turbine 审中-公开
标题翻译：燃气涡轮机燃烧装置
公开(公告)号：JP2005241178A
公开(公告)日：2005-09-08
申请号：JP2004053420
申请日：2004-02-27
申请人： Kawasaki Heavy Ind Ltd , 川崎重工業株式会社
发明人： MATSUMOTO TADASHI , DOURA YASUSHI , OGATA MASAHIRO
IPC分类号： F23R3/28 , F02C7/22
摘要： PROBLEM TO BE SOLVED: To provide a combustion device of a gas turbine excellent in flame keeping properties for stably keeping flame by forming a back-flow area of mixed gas in a combustion chamber in a well-balanced manner without irregularity in intensity.
SOLUTION: At a top part of an inner cylinder 10 of the combustion device, a plurality of first fuel injection holes 26 for injecting fuel F to the combustion chamber C are coaxially provided with the inner cylinder 10. For the first fuel injection holes 26, inside/outside air passages 28, 29 for supplying air CA to the combustion chamber C are provided inside and outside of the inner cylinder in a diameter direction. Part of fuel F is injected from the second fuel injection holes 32 to the inner air passage 28.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种具有优异的火焰保持性能的燃气轮机的燃烧装置，用于通过以良好的平衡方式在燃烧室中形成混合气体的回流区域来稳定地保持火焰，而没有不规则的强度。解决方案：在燃烧装置的内筒10的顶部，将多个用于将燃料F喷射到燃烧室C的第一燃料喷射孔26与内筒10同轴设置。对于第一燃料喷射在内筒的内径和外侧沿直径方向设置有用于向燃烧室C供给空气CA的内部/外部空气通道28,29的孔26。燃料F的一部分从第二燃料喷射孔32喷射到内部空气通道28.版权所有（C）2005，JPO＆NCIPI

6. 发明专利

JPH08210641A BURNER FOR GAS TURBINE AND GAS TURBINE COMBUSTION SYSTEM USING THE SAME 失效
公开(公告)号：JPH08210641A
公开(公告)日：1996-08-20
申请号：JP3765095
申请日：1995-02-01
申请人： KAWASAKI HEAVY IND LTD
发明人： KAJITA SHINICHI , OGA SHINICHI , OGATA MASAHIRO , KITAJIMA JUNICHI , KIMURA TAKEKIYO
IPC分类号： F02C9/34 , F23R3/28 , F23R3/34
摘要： PURPOSE: To perform the high burning efficiency under a simple control and low NOx while suppressing the diameter and length sizes by forming first and second burning areas in a combustion chamber and providing first and second burners therein. CONSTITUTION: A burner 2 burns compressed air supplied from a compressor and supplies it to a turbine. In this case, the burner 2 comprises a plurality of first burners 19a, 19h for forming a first burning area 11a in a combustion chamber 11 at the same position of the chamber 11 in the axial central direction at the upstream side of the chamber 11. The burner 2 further comprises a second burner 40 for forming a second burning area 11b in the chamber 11 at the downstream side of the area 11a in the chamber 11. Further, the burner 40 is disposed oppositely to a diluting air hole 38 for introducing the air into the chamber 11 at the downstream side of the first area 11a. Further, in the high load area of the turbine, there is provided a fuel controller for supplying 25% or less of the fuel flow rate from the burner 40.

7. 发明专利

JPH10300090A GAS TURBINE WITH PRE-MIXING TYPE COMBUSTION DEVICE 失效
公开(公告)号：JPH10300090A
公开(公告)日：1998-11-13
申请号：JP11391497
申请日：1997-05-01
申请人： KAWASAKI HEAVY IND LTD
发明人： KAJITA SHINICHI , OGATA MASAHIRO
IPC分类号： F23R3/16 , F23R3/28 , F23R3/30 , F23R3/32 , F23R3/34
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine having a pre-mixing type combustion device in which carbon is not adhered and accumulated at a wall surface of a premixing chamber and liquid fuel adhered to the wall surface of the pre-mixing chamber is prevented from flowing to the combustion device. SOLUTION: This gas turbine provided with a pre-mixing type combustion device is comprised of a pilot nozzle 24 for supplying fuel to compressed air supplied from a compressor to ignite fuel, an annular pre-mixing chamber 27 arranged at an outer circumference of the pilot nozzle 24, a main nozzle 29 for supplying pre-mixing fuel to the pre-mixing chamber 27, wherein there is provided a combustion device 5 for keeping an outer circumferential surface of an inner circumferential wall 27c higher than a carbon adhering temperature by covering at least a part of the outer circumference of a diffusion combustion region S1 through the pilot nozzle 24.

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