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1. 发明公开

US20230374906A1 HIGH-TEMPERATURE PART AND GAS TURBINE INCLUDING THE SAME 审中-公开
公开(公告)号：US20230374906A1
公开(公告)日：2023-11-23
申请号：US18197231
申请日：2023-05-15
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Masahiro WATANABE , Taiki KINOSHITA , Kiyoshi FUJIMOTO , Sosuke NAKAMURA , Norihiko MOTOYAMA , Kenichi HASHIMOTO , Akito KIRA
IPC分类号： F01D5/28 , F01D11/00
CPC分类号： F01D5/288 , F01D11/003 , F05D2230/90 , F05D2300/611
摘要： A high-temperature part of the present disclosure includes: a high-temperature part body which includes a base and a coating layer formed on a part of a surface of the base; and a protective layer which is formed on at least a part of a surface of the coating layer. The protective layer is formed of a material which is allowed to disappear from a surface of the coating layer under an operation environment of a gas turbine.

2. 发明公开

US20230228421A1 FUEL INJECTOR, COMBUSTOR INCLUDING THE FUEL INJECTOR, AND GAS TURBINE INCLUDING THE COMBUSTOR 审中-公开
公开(公告)号：US20230228421A1
公开(公告)日：2023-07-20
申请号：US17928771
申请日：2021-06-21
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： Kiyoshi FUJIMOTO , Shinichi FUKUBA , Mitsuhiro NAKAO , Yoshikazu MATSUMURA , Kota YOSHINO , Satoshi TAKIGUCHI , Sosuke NAKAMURA , Shinji AKAMATSU
IPC分类号： F23R3/28 , F02C7/22 , F23R3/16 , F23R3/32
CPC分类号： F23R3/286 , F02C7/22 , F23R3/16 , F23R3/32 , F05D2220/32 , F05D2240/35
摘要： A fuel injector has a body extending in an axial direction. The body includes: an axial passage formed so as to extend in the axial direction; a radial passage formed so as to communicate at one end with the axial passage and to open at another end to an outer surface of the body; and an internal passage including a first opening and a second opening open to the outer surface, and formed so as to extend inside the body from the first opening to the second opening. The first opening and the second opening are located opposite to each other across a third opening, through which the radial passage opens to the outer surface, in a circumferential direction centered on an axis of the body.

3. 发明公开

US20240125476A1 GAS TURBINE COMBUSTOR AND GAS TURBINE 审中-公开
公开(公告)号：US20240125476A1
公开(公告)日：2024-04-18
申请号：US18269115
申请日：2021-12-28
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Kenji MIYAMOTO , Sosuke NAKAMURA , Taku EGAWA , Tomo KAWAKAMI
IPC分类号： F23R3/36 , F02C9/40 , F23R3/26
CPC分类号： F23R3/36 , F02C9/40 , F23R3/26 , F05D2240/35 , F05D2270/303
摘要： A gas turbine combustor according to at least one embodiment, includes: a less combustible fuel flow control part for controlling, independently of each other, amounts of less combustible fuel supplied to a first fuel injector and a second fuel injector; a highly combustible fuel flow control part for controlling, independently of each other, amounts of highly combustible fuel having a higher combustion speed than the less combustible fuel and supplied to the first fuel injector and the second fuel injector; and a controller configured to control the less combustible fuel flow control part and the highly combustible fuel flow control part such that a relative ratio of a first ratio of the highly combustible fuel to whole of first fuel injected by the first fuel injector and a second ratio of the highly combustible fuel to whole of second fuel injected by the second fuel injector changes according to an operating condition of a gas turbine.

4. 发明公开

US20230313994A1 COMBUSTOR AND GAS TURBINE 审中-公开
公开(公告)号：US20230313994A1
公开(公告)日：2023-10-05
申请号：US18117127
申请日：2023-03-03
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Taku EGAWA , Sosuke NAKAMURA , Tomo KAWAKAMI , Yoshitaka HIRATA , Yoshinori MATSUBARA , Tatsuya HAGITA
IPC分类号： F23R3/28 , F23R3/26
CPC分类号： F23R3/286 , F23R3/26
摘要： A combustor of the present disclosure includes: a mixing portion which is provided with a plurality of mixing passages passing through the mixing portion so as to be extended from an upstream end surface to a downstream end surface of the mixing portion intersecting an axis of the combustor, air being introduced to the plurality of the mixing passages from the upstream end surface of the mixing portion; and a fuel supply portion which is configured to supply the air introduced to the mixing passages with fuel to generate mixed fluid, wherein flow paths of the mixing passages have different pressure loss coefficients so that the differences in the flow velocity of the mixed fluid flowing through the mixing passages at the downstream end surface of the mixing portion are greater than those of a case where the mixing passages have the same flow path shape.

5. 发明申请

US20140190176A1 FUEL CONTROL METHOD AND FUEL CONTROL APPARATUS FOR GAS TURBINE AND GAS TURBINE 有权
标题翻译：燃油控制方法和燃油控制装置用于气体涡轮机和气体涡轮机
公开(公告)号：US20140190176A1
公开(公告)日：2014-07-10
申请号：US14203414
申请日：2014-03-10
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Sosuke NAKAMURA , Satoshi TANIMURA , Shinji AKAMATSU , Shinsuke NAKAMURA , Takashi SONODA , Akihiko SAITO , Makoto KISHI
IPC分类号： F02C9/26
CPC分类号： F02C9/26 , F02C9/34 , F05D2270/082 , F23K5/005 , F23R3/286 , F23R3/36
摘要： A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced. Because fuel is supplied from the main nozzles of all groups and burned in the entire area of the combustor upon ignition, it is possible to easily propagate a flame to all the other adjacent main nozzle groups, thereby improving the ignition characteristics of the whole gas turbine.
摘要翻译：一种用于具有燃烧器的燃气轮机的燃料控制方法，所述燃气轮机由至少两组用于供应燃料的主喷嘴组成，并且在燃烧器（S1）点火时从所有组的主喷嘴供应燃料，并且供应在燃气轮机的后续加速期间来自组A的三个主喷嘴的燃料（S3）。由于在加速期间从少量主喷嘴喷射燃料，所以每个主喷嘴的燃料流量增加，从而提高燃烧区域的燃料空气比（燃料流量/空气流量），提高燃烧特点因此，一氧化碳和未燃碳氢化合物的产生减少，由此不需要旁通阀并且降低制造成本。因为燃料从所有组的主喷嘴供应并且在点火时在燃烧器的整个区域燃烧，所以可以容易地将火焰传播到所有其他相邻的主喷嘴组，从而提高整个燃气轮机的点火特性。

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