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1. 发明授权

US09528706B2 Swirling midframe flow for gas turbine engine having advanced transitions 有权
标题翻译：具有高级过渡的燃气涡轮发动机的旋转中架流
公开(公告)号：US09528706B2
公开(公告)日：2016-12-27
申请号：US14105313
申请日：2013-12-13
申请人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
发明人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
IPC分类号： F23R3/46 , F04D29/54 , F23R3/02 , F23R3/04 , F23R3/42
CPC分类号： F23R3/46 , F04D29/542 , F04D29/545 , F04D29/547 , F23R3/02 , F23R3/04 , F23R3/425
摘要： A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.
摘要翻译：一种燃气涡轮发动机罐环式燃烧装置（10），包括：轴向压缩机（82），其可操作以沿旋转方向（60）旋转; 构造成从所述轴向压缩机接收压缩空气（16）的扩散器（100,110）; 配置成从扩散器接收压缩空气的增压室（22）多个燃烧器罐（12）各自具有与所述气室流体连通的燃烧器入口（38），其中每个燃烧室可以被切向地定向，使得相应的燃烧器入口在与旋转相反的方向上与相应的燃烧室出口周向偏移方向; 以及气流引导装置（80），其构造成沿着与旋转方向相反的方向对所述增压室中的压缩空气施加周向运动。

2. 发明申请

US20150167986A1 SWIRLING MIDFRAME FLOW FOR GAS TURBINE ENGINE HAVING ADVANCED TRANSITIONS 有权
标题翻译：用于具有高级过渡的气体涡轮发动机的旋转中间流
公开(公告)号：US20150167986A1
公开(公告)日：2015-06-18
申请号：US14105313
申请日：2013-12-13
申请人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
发明人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
IPC分类号： F23R3/46
CPC分类号： F23R3/46 , F04D29/542 , F04D29/545 , F04D29/547 , F23R3/02 , F23R3/04 , F23R3/425
摘要： A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.
摘要翻译：一种燃气涡轮发动机罐环式燃烧装置（10），包括：轴向压缩机（82），其可操作以沿旋转方向（60）旋转; 构造成从所述轴向压缩机接收压缩空气（16）的扩散器（100,110）; 配置成从扩散器接收压缩空气的增压室（22）多个燃烧器罐（12）各自具有与所述气室流体连通的燃烧器入口（38），其中每个燃烧室可以被切向地定向，使得相应的燃烧器入口在与旋转相反的方向上与相应的燃烧室出口周向偏移方向; 以及气流引导装置（80），其构造成沿着与旋转方向相反的方向对所述增压室中的压缩空气施加周向运动。

3. 发明授权

US08276389B2 Assembly for directing combustion gas 有权
标题翻译：用于引导燃烧气体的组件
公开(公告)号：US08276389B2
公开(公告)日：2012-10-02
申请号：US13096041
申请日：2011-04-28
申请人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
发明人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
IPC分类号： F02C3/00
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F23R3/425 , F23R3/46 , F23R3/60
摘要： An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented concentric to a gas turbine engine longitudinal axis (20) upstream of the turbine first stage blade section. Each respective IEP (16) includes a first flow path section (40) receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis (22) there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (42). Each respective IEP further includes a second flow path section (112) receiving a partially bounded second flow from an upstream adjacent IEP (66) and delivering at least part of the second flow to the turbine first stage blade section.
摘要翻译：一种用于将燃烧气体从多个罐环形燃烧器输送到燃气涡轮发动机的涡轮机第一级叶片部分的装置（10），所述装置（10）包括多个互连的集成出口件（IEP）部分（16），其限定与涡轮机第一级叶片部分上游的燃气涡轮发动机纵向轴线（20）同心取向的环形室（18）。每个相应的IEP（16）包括第一流路部分（40），其沿着相应的公共轴线（22）接收并完全限定来自相应的罐环形燃烧器的第一流动，并且将部分有界的第一流体递送到下游相邻 IEP部分（42）。每个相应的IEP还包括第二流路部分（112），其接收来自上游相邻的IEP（66）的部分界定的第二流，并将第二流的至少一部分输送到涡轮机第一级叶片部分。

4. 发明申请

US20110203282A1 ASSEMBLY FOR DIRECTING COMBUSTION GAS 有权
标题翻译：组装燃烧燃气
公开(公告)号：US20110203282A1
公开(公告)日：2011-08-25
申请号：US13096041
申请日：2011-04-28
申请人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
发明人： Richard C. Charron , Raymond S. Nordlund , Jay A. Morrison , Ernie B. Campbell , Daniel J. Pierce , Matthew D. Montgomery , Jody W. Wilson
IPC分类号： F02C3/14
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/121 , F05D2250/141 , F05D2250/322 , F05D2250/323 , F23R3/425 , F23R3/46 , F23R3/60
摘要： An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented concentric to a gas turbine engine longitudinal axis (20) upstream of the turbine first stage blade section. Each respective IEP (16) includes a first flow path section (40) receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis (22) there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (42). Each respective IEP further includes a second flow path section (112) receiving a partially bounded second flow from an upstream adjacent IEP (66) and delivering at least part of the second flow to the turbine first stage blade section.
摘要翻译：一种用于将燃烧气体从多个罐环形燃烧器输送到燃气涡轮发动机的涡轮机第一级叶片部分的装置（10），所述装置（10）包括多个互连的集成出口件（IEP）部分（16），其限定与涡轮机第一级叶片部分上游的燃气涡轮发动机纵向轴线（20）同心取向的环形室（18）。每个相应的IEP（16）包括第一流路部分（40），其沿着相应的公共轴线（22）接收并完全限定来自相应的罐环形燃烧器的第一流动，并且将部分有界的第一流体递送到下游相邻 IEP部分（42）。每个相应的IEP还包括第二流路部分（112），其接收来自上游相邻的IEP（66）的部分界定的第二流，并将第二流的至少一部分输送到涡轮机第一级叶片部分。

5. 发明授权

US09127554B2 Gas turbine engine with radial diffuser and shortened mid section 有权
标题翻译：具有径向扩散器和缩短中段的燃气轮机
公开(公告)号：US09127554B2
公开(公告)日：2015-09-08
申请号：US13602422
申请日：2012-09-04
申请人： Richard C. Charron , Matthew D. Montgomery
发明人： Richard C. Charron , Matthew D. Montgomery
IPC分类号： F01D9/02 , F01D9/04 , F02C3/14 , F23R3/46
CPC分类号： F01D9/023 , F01D9/02 , F01D9/04 , F02C3/14 , F23R3/46 , Y02T50/671
摘要： An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130, 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward.
摘要翻译：一种工业燃气涡轮发动机（10），包括：罐式环形燃烧组件（80），其具有多个离散的流动管道，其构造成从相应燃烧器（82）接收燃烧气体，并沿着直线流动路径适于直接输送到涡轮叶片（62）的第一排（56）上的速度和方位; 和压缩机扩散器（32），其具有被配置为接收压缩空气的轴向流动并将径向向外的压缩空气的轴向流动重定向的重定向表面（130,140）。

6. 发明授权

US09470422B2 Gas turbine structural mounting arrangement between combustion gas duct annular chamber and turbine vane carrier 有权
标题翻译：燃气轮机环形腔和涡轮叶片架之间的燃气轮机结构安装
公开(公告)号：US09470422B2
公开(公告)日：2016-10-18
申请号：US14059521
申请日：2013-10-22
申请人： David J. Wiebe , Richard C. Charron , Jay A. Morrison
发明人： David J. Wiebe , Richard C. Charron , Jay A. Morrison
IPC分类号： F23R3/60 , F01D9/02 , F23R3/46
CPC分类号： F23R3/60 , F01D9/023 , F05D2260/30 , F23R3/46
摘要： A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors and to deliver the discrete flows to a turbine inlet annulus, wherein the annular chamber includes an inner diameter (52) and an outer diameter (60); an outer diameter mounting arrangement (34) configured to permit relative radial movement and to prevent relative axial and circumferential movement between the outer diameter and a turbine vane carrier (20); and an inner diameter mounting arrangement (36) including a bracket (64) secured to the turbine vane carrier, wherein the bracket is configured to permit the inner diameter to move radially with the outer diameter and prevent axial deflection of the inner diameter with respect to the outer diameter.
摘要翻译：一种燃气涡轮发动机管道装置（10），包括：环形室（14），其构造成容纳源自相应罐燃烧器的多个不连续的燃烧气体流，并将离散流输送到涡轮入口环，其中环形室包括内径（52）和外径（60）; 外径安装装置（34）被构造成允许相对径向移动并且防止外径与涡轮叶片载体（20）之间的相对轴向和周向移动; 以及内径安装装置（36），其包括固定到所述涡轮机叶片承载件的支架（64），其中所述支架构造成允许所述内径径向与所述外径径向移动，并且防止所述内径相对于外径。

7. 发明申请

US20120121381A1 TURBINE TRANSITION COMPONENT FORMED FROM AN AIR-COOLED MULTI-LAYER OUTER PANEL FOR USE IN A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的空气冷却多层外板组成的涡轮转换部件
公开(公告)号：US20120121381A1
公开(公告)日：2012-05-17
申请号：US12945943
申请日：2010-11-15
申请人： Richard C. Charron , Daniel J. Pierce , Jay A. Morrison , Ching-Pang Lee , Kenneth K. Landis , Walter Marussich
发明人： Richard C. Charron , Daniel J. Pierce , Jay A. Morrison , Ching-Pang Lee , Kenneth K. Landis , Walter Marussich
IPC分类号： F03B11/00
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201 , F23R2900/03044
摘要： A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.
摘要翻译：公开了一种用于将来自燃烧器的气流引导到燃气涡轮发动机中的涡轮部分的第一级的过渡管道的冷却系统。过渡管道可以具有由内板形成的多面板外壁，该内板具有限定热气路径气室的至少一部分的内表面和从内板径向向外定位的中间板，使得至少一个冷却室形成在内板和中间板之间。过渡管还可以包括外板。内部，中间和外部面板可以包括一个或多个计量孔，用于在冷却室之间通过冷却流体以冷却面板。中间板和外板可以用连接系统固定到内板上，使得中间板和外板可在平面内移动。

8. 发明申请

US20140060000A1 GAS TURBINE ENGINE WITH RADIAL DIFFUSER AND SHORTENED MID SECTION 有权
标题翻译：燃气涡轮发动机带有径向发生器和中空部分
公开(公告)号：US20140060000A1
公开(公告)日：2014-03-06
申请号：US13602422
申请日：2012-09-04
申请人： Richard C. Charron , Matthew D. Montgomery
发明人： Richard C. Charron , Matthew D. Montgomery
IPC分类号： F02C3/14 , F02C7/00
CPC分类号： F01D9/023 , F01D9/02 , F01D9/04 , F02C3/14 , F23R3/46 , Y02T50/671
摘要： An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130, 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward.
摘要翻译：一种工业燃气涡轮发动机（10），包括：罐式环形燃烧组件（80），其具有多个离散的流动管道，其构造成从相应燃烧器（82）接收燃烧气体，并沿着直线流动路径适于直接输送到涡轮叶片（62）的第一排（56）上的速度和方位; 和压缩机扩散器（32），其具有被配置为接收压缩空气的轴向流动并将径向向外的压缩空气的轴向流动重定向的重定向表面（130,140）。

9. 发明授权

US09097117B2 Turbine transition component formed from an air-cooled multi-layer outer panel for use in a gas turbine engine 有权
标题翻译：由用于燃气涡轮发动机的风冷多层外板形成的涡轮转换部件
公开(公告)号：US09097117B2
公开(公告)日：2015-08-04
申请号：US12945943
申请日：2010-11-15
申请人： Richard C. Charron , Daniel J. Pierce , Jay A. Morrison , Ching-Pang Lee , Kenneth K. Landis , Walter Marussich
发明人： Richard C. Charron , Daniel J. Pierce , Jay A. Morrison , Ching-Pang Lee , Kenneth K. Landis , Walter Marussich
IPC分类号： F23R3/46 , F01D9/02 , F01D25/12
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201 , F23R2900/03044
摘要： A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.
摘要翻译：公开了一种用于将来自燃烧器的气流引导到燃气涡轮发动机中的涡轮部分的第一级的过渡管道的冷却系统。过渡管道可以具有由内板形成的多面板外壁，该内板具有限定热气路径气室的至少一部分的内表面和从内板径向向外定位的中间板，使得至少一个冷却室形成在内板和中间板之间。过渡管还可以包括外板。内部，中间和外部面板可以包括一个或多个计量孔，用于在冷却室之间通过冷却流体以冷却面板。中间板和外板可以用连接系统固定到内板上，使得中间板和外板可在平面内移动。

10. 发明申请

US20150107264A1 STRUCTURAL MOUNTING ARRANGEMENT FOR GAS TURBINE ENGINE COMBUSTION GAS DUCT 有权
标题翻译：气体涡轮发动机燃烧气体结构安装布置
公开(公告)号：US20150107264A1
公开(公告)日：2015-04-23
申请号：US14059521
申请日：2013-10-22
申请人： David J. Wiebe , Richard C. Charron , Jay A. Morrison
发明人： David J. Wiebe , Richard C. Charron , Jay A. Morrison
IPC分类号： F23R3/60 , F01D9/02
CPC分类号： F23R3/60 , F01D9/023 , F05D2260/30 , F23R3/46
摘要： A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors and to deliver the discrete flows to a turbine inlet annulus, wherein the annular chamber includes an inner diameter (52) and an outer diameter (60); an outer diameter mounting arrangement (34) configured to permit relative radial movement and to prevent relative axial and circumferential movement between the outer diameter and a turbine vane carrier (20); and an inner diameter mounting arrangement (36) including a bracket (64) secured to the turbine vane carrier, wherein the bracket is configured to permit the inner diameter to move radially with the outer diameter and prevent axial deflection of the inner diameter with respect to the outer diameter.
摘要翻译：一种燃气涡轮发动机管道装置（10），包括：环形室（14），其构造成容纳来自相应罐式燃烧器的多个不连续的燃烧气体流并且将离散流输送到涡轮机入口环，其中环形室包括内径（52）和外径（60）; 外径安装装置（34）被构造成允许相对径向移动并且防止外径与涡轮叶片载体（20）之间的相对轴向和周向移动; 以及内径安装装置（36），其包括固定到所述涡轮机叶片承载件的支架（64），其中所述支架构造成允许所述内径径向与所述外径径向移动，并且防止所述内径相对于外径。

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