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1. 发明申请

WO2022214384A1 COMBUSTOR FOR A GAS TURBINE 审中-公开
公开(公告)号：WO2022214384A1
公开(公告)日：2022-10-13
申请号：PCT/EP2022/058581
申请日：2022-03-31
申请人： SIEMENS ENERGY GLOBAL GMBH & CO. KG
发明人： PARSANIA, Nishant
IPC分类号： F23R3/28 , F23R3/34 , F23R3/14 , F23R3/16
摘要： A combustor (100) for a gas turbine comprising a combustion chamber (102) having an inlet (104). The combustion chamber inlet (104) is defined by a burner (30). The burner comprises a pilot burner section (200) centred on the centre axis (Y); a swirler section (300) comprising vanes (302) which extend radially outwards from the pilot burner section (200); and a main burner section (400) which extends radially outwards from, and surrounds, the swirler section (300).

2. 发明申请

WO2022152622A1 BURNER 审中-公开
公开(公告)号：WO2022152622A1
公开(公告)日：2022-07-21
申请号：PCT/EP2022/050242
申请日：2022-01-07
申请人： CROSSTOWN POWER GMBH
发明人： HELLAT, Jaan , KAPPIS, Wolfgang Dieter , HARASGAMA, Sriwickrama Prithiviraj , GENIN, Franklin Marie Georges Martin , SYED, Khawar
IPC分类号： F23R3/28 , F23R3/14 , F23D14/02
摘要： A microtube cluster burner (1) comprises a multitude of ducts (41) extending through fluid plenums (31, 32, 33). Discharge means (51, 52) fluidly connect the plenums to the ducts. At least one of the ducts (41) is provided with at least two discharge means (51, 52) for discharging fluid from a plenum (31, 32) into the duct at at least two different longitudinal positions of the duct.

3. 发明申请

WO2022043079A1 COMBUSTOR FOR A GAS TURBINE 审中-公开
公开(公告)号：WO2022043079A1
公开(公告)日：2022-03-03
申请号：PCT/EP2021/072492
申请日：2021-08-12
申请人： SIEMENS ENERGY GLOBAL GMBH & CO. KG
发明人： SADASIVUNI, Suresh
IPC分类号： F23R3/34 , F23R3/36 , F23R3/14
摘要： A combustor (36) for a gas turbine, the combustor (36) comprising a combustor axis (44) about which is arranged in flow sequence a radial swirler (40), a pre-chamber (42) and a combustion chamber (38). The radial swirler (40) comprises a base plate (45), an annular array of swirler vanes (46), defining swirler slots (47), arranged around the base plate (45), a main fuel injector (48A, 48B) for injecting a main fuel and a pilot fuel injector (50) for injecting a pilot fuel. The combustor comprises a premixer nozzle (70) located on the combustion chamber (38). The premixer nozzle (70) comprising a housing (78), an array of tubes (80) within the housing (78) and a first fuel gallery (72) for supplying a first fuel (83). Each tube (80) of the array of tubes (80) comprising an inlet (86), an outlet (88), a first aperture (90) and a second aperture (92). The first fuel gallery (72) is arranged to supply the first fuel (83) to the first aperture (90) and / or the second aperture (92). In use, air (34) is supplied to the combustor and a first portion of the air (34A) passes through the radial swirler (40) and a second portion of the air (34B) passes through the tubes (80) of the array of tubes (80) from inlet (86) to outlet (88) and mixes with the first fuel (83) that passes through the first aperture (90) and / or the second aperture (92).

4. 发明申请

WO2022015321A1 PREMIXER INJECTOR ASSEMBLY IN GAS TURBINE ENGINE 审中-公开
公开(公告)号：WO2022015321A1
公开(公告)日：2022-01-20
申请号：PCT/US2020/042489
申请日：2020-07-17
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： VERSAILLES, Philippe , WATSON, Graeme , FURI, Marc
IPC分类号： F23R3/14 , F23R3/28
摘要： A premixer injector assembly in a gas turbine engine includes at least one premixer injector. The premixer injector includes a fuel tube having a fuel feed passage enclosed by an outer surface, a plurality of fins coupled to the fuel tube extending from the outer surface of the fuel feed passage, the outer surface of the fuel feed passage between adjacent fins having a concave shape, a plurality of mixing channels defined between adjacent fins, a plurality of fuel injection apertures disposed along the fuel feed passage to direct fuel from the fuel feed passage to the mixing channels, an air tube coupled to the fuel tube to at least partially enclose the fuel tube, and a plurality of air injection openings arranged along the air tube to inject air to the mixing channels.

5. 发明申请

WO2020124049A1 METHOD AND SYSTEMS FOR A FLUIDIC VARIABLE TURBOCHAGER FOR AN ENGINE 审中-公开
公开(公告)号：WO2020124049A1
公开(公告)日：2020-06-18
申请号：PCT/US2019/066400
申请日：2019-12-13
申请人： TRANSPORTATION IP HOLDINGS, LLC
发明人： KOBIELSKI, Louis , UYGUN, Baris , FELTON, Adam
IPC分类号： F02B37/24 , F23R3/28 , F23R3/14 , F01D17/16
摘要： Various methods and systems are provided for a fluidic variable turbine. In one example, a system for an engine comprises a turbocharger turbine including a nozzle ring, the nozzle ring including a plurality of stationary vanes, each vane of the plurality of stationary vanes including a plurality of injection ports arranged at an outer surface of the vane, and a gas supply system to supply variable gas flow to and out of the plurality of injection ports.

6. 发明申请

WO2020071399A1 航空機用のアニュラ型ガスタービン燃焼器审中-公开
公开(公告)号：WO2020071399A1
公开(公告)日：2020-04-09
申请号：PCT/JP2019/038850
申请日：2019-10-02
申请人：川崎重工業株式会社 , 国立研究開発法人宇宙航空研究開発機構
发明人：松山　竜佐 , 吉田　征二 , 藤原　仁志
IPC分类号： F23R3/16 , F02C7/24 , F23R3/14 , F23R3/28
摘要：航空機用のアニュラ型ガスタービン燃焼器は、燃料噴射装置配置空間において燃料噴射装置の径方向に前記燃料噴射装置と並んで配置され、共振室を有する複数のレゾネータを備える。前記燃焼室と前記燃料噴射装置配置空間とを区分けするバルクヘッドは、前記複数のレゾネータの前記共振室と前記燃焼室との間に配置された複数の開口を有する。前記共振室は、前記開口により前記燃焼室に連通している。前記共振室の少なくとも一部は、前記燃料噴射装置の軸線方向から見て前記アウターライナの最大外径部よりも径方向内側に配置されている。

7. 发明申请

WO2019194817A1 PREMIXER FOR LOW EMISSIONS GAS TURBINE COMBUSTOR 审中-公开
公开(公告)号：WO2019194817A1
公开(公告)日：2019-10-10
申请号：PCT/US2018/026431
申请日：2018-04-06
申请人： GENERAL ELECTRIC COMPANY
发明人： THARIYAN, Mathew Paul , GIRIDHARAN, Manampathy Gangadharan , SINGH, Kapil Kumar , KAPILAVAI, Sravan Kumar Dheeraj , MCMANUS, Keith Robert , BOARDMAN, Gregory Allen , DURBIN, Mark David
IPC分类号： F23R3/28 , F23R3/14
摘要： A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rotate air in an opposite direction. The inner swirler vanes and the outer swirler vanes are separated by an annular splitter. The outer swirler vanes define an outlet plane, and the inner swirler vanes each have a trailing edge that is disposed at an acute angle relative to the outlet plane. In one aspect, the inner swirler is axially offset from the outer swirler. The mixing duct may also define fuel passages that deliver fuel to fuel outlets on the downstream end of the mixing duct. The premixer is designed for operation on gaseous fuel or liquid fuel.

8. 发明申请

WO2018168747A1 燃焼器用ノズル、燃焼器、及びガスタービン审中-公开
公开(公告)号：WO2018168747A1
公开(公告)日：2018-09-20
申请号：PCT/JP2018/009444
申请日：2018-03-12
申请人：三菱日立パワーシステムズ株式会社
发明人：宮本　健司 , 谷口　健太 , 井上　慶 , 道免　昌平 , 市川　雄一 , 谷村　聡
IPC分类号： F23R3/28 , F02C3/22 , F02C3/24 , F02C7/22 , F23R3/14 , F23R3/32
摘要：軸線に沿って延びるノズル本体（２）を備え、ノズル本体（２）は、軸線（Ａｍ）に沿って形成され、第一の燃料（Ｆ１）が流通する第一燃料通路（２１）と、第一燃料通路（２１）から先端側に向かうにしたがってノズル本体の外周面に延びて、外周面から第一の燃料を噴出する第一燃料噴出路（２２）と、第一燃料通路（２１）よりも軸線の径方向外側で軸線方向（Ｄａ）に延びて、パージ空気（ＰＡ）が流通する空気流通路（２４）と、空気流通路（２４）からノズル本体（２）の先端中央に向かって延びて、先端中央からパージ空気（ＰＡ）を噴出する空気噴出路（２５）と、を備える燃焼器用ノズルを提供する。

9. 发明申请

WO2017111041A1 燃料噴射装置审中-公开
标题翻译：喷油器
公开(公告)号：WO2017111041A1
公开(公告)日：2017-06-29
申请号：PCT/JP2016/088413
申请日：2016-12-22
申请人：川崎重工業株式会社
发明人：松山　竜佐 , 小田　剛生 , 藤原　仁志
IPC分类号： F23R3/28 , F23R3/14 , F23R3/30
CPC分类号： F23R3/14 , F23R3/28 , F23R3/30
摘要：燃料噴射装置のメイン燃料噴射部は、径方向外方に開口する入口部から圧縮空気を取り込むメイン外側空気流路と、径方向内方に開口する入口部から圧縮空気を取り込むメイン内側空気流路と、メイン外側空気流路が取り込んだ圧縮空気とメイン内側空気流路が取り込んだ圧縮空気が合流する合流空気流路と、メイン外側空気流路が取り込んだ圧縮空気又はメイン内側空気流路が取り込んだ圧縮空気に燃料を噴射するメイン燃料噴射孔と、を有する。
摘要翻译：所述的主燃料喷射部
燃料喷射器，压缩和用于从径向向外从所述入口打开入口取压缩空气主外空气通道，其径向向内打开主内部风路取入空气，压缩空气，并通过在主外空气通道的压缩空气采取合并捕捉的主内部风路的合流空气流路，通过主外空气通道捕获压缩空气或者用于将燃料喷射入由主内部空气流动路径吸入的压缩空气中的主燃料喷射孔。

10. 发明申请

WO2017052547A1 DUAL STAGE VANE PILOT NOZZLE 审中-公开
标题翻译：双级风向导喷嘴
公开(公告)号：WO2017052547A1
公开(公告)日：2017-03-30
申请号：PCT/US2015/051884
申请日：2015-09-24
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： BERTONCELLO, James , MIDUTURI, Krishna C. , RITLAND, David M , ZURHORST, Marcus , WEGNER, Bernhard , HUTH, Michael
IPC分类号： F23R3/28 , F23R3/14 , F23C7/00
CPC分类号： F23R3/286 , F23C7/004 , F23C2900/07001 , F23D2900/11402 , F23R3/14
摘要： A dual stage vane pilot nozzle (100) has a non-diffusion nozzle (110) and a first fuel stage (121) and a second fuel stage (122). The first fuel stage (121) has a first fuel injector (101) having first injection holes (103) and a first fuel annulus (105). The second fuel stage (122) has a second fuel injector (102) having second injection holes (104) and a second fuel annulus (106). The non-diffusion (110) does not have a diffusion tip. This arrangement allows for the reduction of nitrogen oxide emissions.
摘要翻译：双级叶片先导喷嘴（100）具有非扩散喷嘴（110）和第一燃料级（121）和第二燃料级（122）。第一燃料台（121）具有第一燃料喷射器（101），其具有第一喷射孔（103）和第一燃料环（105）。第二燃料台（122）具有第二燃料喷射器（102），其具有第二喷射孔（104）和第二燃料环（106）。非扩散（110）不具有扩散尖端。这种布置允许减少氮氧化物排放。

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