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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. 发明授权

US09388738B2 Casing for a gas turbine engine 有权
标题翻译：套管燃气轮机
公开(公告)号：US09388738B2
公开(公告)日：2016-07-12
申请号：US13252325
申请日：2011-10-04
申请人： David J. Wiebe , David A. Little , Richard C. Charron
发明人： David J. Wiebe , David A. Little , Richard C. Charron
IPC分类号： F01D9/02 , F02C3/14 , F23R3/46 , F23R3/02
CPC分类号： F02C3/14 , F01D9/023 , F23R3/02 , F23R3/46
摘要： A casing for a can annular gas turbine engine, including: a compressed air section (40) spanning between a last row of compressor blades (26) and a first row of turbine blades (28), the compressed air section (40) having a plurality of openings (50) there through, wherein a single combustor/advanced duct assembly (64) extends through each opening (50); and one top hat (68) associated with each opening (50) configured to enclose the associated combustor/advanced duct assembly (64) and seal the opening (50). A volume enclosed by the compressed air section (40) is not greater than a volume of a frustum (54) defined at an upstream end (56) by an inner diameter of the casing at the last row of compressor blades (26) and at a downstream end (60) by an inner diameter of the casing at the first row of turbine blades (28).
摘要翻译：一种用于罐式环形燃气涡轮发动机的壳体，包括：压缩空气部分（40），跨过最后一排压缩机叶片（26）和第一排涡轮叶片（28），压缩空气部分（40）具有多个开口（50）穿过其中，其中单个燃烧器/先进管道组件（64）延伸穿过每个开口（50）; 以及与每个开口（50）相关联的一个顶帽（68），其构造成包围相关联的燃烧器/先进管道组件（64）并密封所述开口（50）。由压缩空气部分（40）包围的体积不大于在上游端（56）处由最后一排压缩机叶片（26）处的壳体的内径限定的平截头体（54）的体积，并且在在第一排涡轮叶片（28）处通过壳体的内径的下游端（60）。

3. 发明授权

US09200565B2 Full hoop casing for midframe of industrial gas turbine engine 有权
标题翻译：工业燃气轮机发动机中框全套环
公开(公告)号：US09200565B2
公开(公告)日：2015-12-01
申请号：US13310855
申请日：2011-12-05
申请人： Gerald A. Myers , Richard C. Charron
发明人： Gerald A. Myers , Richard C. Charron
IPC分类号： F02C3/14 , F01D25/24 , F01D25/28 , F23R3/46
CPC分类号： F02C3/14 , F01D25/24 , F01D25/243 , F01D25/285 , F05D2230/70 , F05D2230/72 , F23R3/46
摘要： A can annular industrial gas turbine engine, including: a single-piece rotor shaft spanning a compressor section (82), a combustion section (84), a turbine section (86); and a combustion section casing (10) having a section (28) configured as a full hoop. When the combustion section casing is detached from the engine and moved to a maintenance position to allow access to an interior of the engine, a positioning jig (98) is used to support the compressor section casing (83) and turbine section casing (87).
摘要翻译：一种罐式环形工业燃气涡轮发动机，包括：跨过压缩机部分（82），燃烧部分（84），涡轮部分（86）的单件转子轴; 和具有构成为完全箍的部分（28）的燃烧部分壳体（10）。当燃烧部分壳体与发动机分离并移动到维修位置以允许进入发动机内部时，定位夹具（98）用于支撑压缩机部分壳体（83）和涡轮部分壳体（87）。

4. 发明授权

US08210819B2 Airfoil structure shim 有权
标题翻译：翼型结构垫片
公开(公告)号：US08210819B2
公开(公告)日：2012-07-03
申请号：US12035495
申请日：2008-02-22
申请人： David J Wiebe , John W Finneran , Jeffery W Samuelson , Richard C Charron
发明人： David J Wiebe , John W Finneran , Jeffery W Samuelson , Richard C Charron
IPC分类号： F04D29/34
CPC分类号： F01D5/3038 , F05D2260/30
摘要： An airfoil structure, shim, and retention member combination includes an airfoil structure, a retention member and a shim. The airfoil structure may define a first recess. The retention member may define a second recess. The first and second recesses may define a cavity. The shim may include a main body and a plurality of first fins extending outwardly from a first side of the main body. The first fins may further extend transverse to a longitudinal axis of the main body. The shim may be positioned in the cavity such that the first fins extend in a direction substantially transverse to a longitudinal axis of the cavity.
摘要翻译：翼型结构，垫片和保持构件组合包括翼型结构，保持构件和垫片。翼型结构可以限定第一凹部。保持构件可以限定第二凹部。第一和第二凹部可以限定空腔。垫片可以包括主体和从主体的第一侧向外延伸的多个第一翅片。第一散热片可以进一步横向于主体的纵向轴线延伸。垫片可以定位在空腔中，使得第一翅片沿着基本上横向于腔的纵向轴线的方向延伸。

5. 发明授权

US07862296B2 Turbine vane securing mechanism 有权
标题翻译：涡轮叶片固定机构
公开(公告)号：US07862296B2
公开(公告)日：2011-01-04
申请号：US11844778
申请日：2007-08-24
申请人： John W. Finneran , Jeffery W. Samuelson , Richard C. Charron
发明人： John W. Finneran , Jeffery W. Samuelson , Richard C. Charron
IPC分类号： F03B3/14
CPC分类号： F01D9/042 , F05B2260/301 , F05D2230/644 , F05D2250/314 , F05D2260/96 , Y10S416/50
摘要： A turbine vane attachment system configured to eliminate movement of a turbine vane relative to a turbine vane carrier. The turbine vane attachment system may include a base attached to a turbine airfoil. The base may be configured to contact a wedge support along a plane that is generally nonparallel and nonorthogonal with a longitudinal axis of the airfoil. A bolt may connect the base with the wedge support. The bolt may change a distance between a channel in the base and an outer bearing surface. The turbine vane may be positioned in a vane carrier such that tongues extending from the vane carrier are positioned in the channels. As the bolt is advanced, the wedge support is moved laterally along the support surface of the base and the channels engage the tongues, thereby preventing movement of the turbine vane.
摘要翻译：涡轮机叶片附接系统，被配置为消除涡轮叶片相对于涡轮叶片承载器的运动。涡轮叶片附接系统可以包括附接到涡轮机翼型的基座。基座可以被构造成沿着与翼型件的纵向轴线大致不平行和非正交的平面接触楔形支撑件。螺栓可以将基座与楔形支撑件连接。螺栓可以改变基座中的通道与外部支承表面之间的距离。涡轮叶片可以定位在叶片载体中，使得从叶片载体延伸的舌片定位在通道中。当螺栓前进时，楔形支撑件沿着基座的支撑表面横向移动，并且通道接合舌片，从而防止涡轮叶片的运动。

6. 发明授权

US09322335B2 Gas turbine combustor exit piece with hinged connections 有权
标题翻译：具有铰接连接的燃气轮机燃烧器出口件
公开(公告)号：US09322335B2
公开(公告)日：2016-04-26
申请号：US13834185
申请日：2013-03-15
申请人： Richard C. Charron , William W. Pankey
发明人： Richard C. Charron , William W. Pankey
IPC分类号： F02C7/20 , F01D9/02 , F23R3/42
CPC分类号： F02C7/20 , F01D9/023 , F05D2250/25 , F23R3/425
摘要： An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (78A, 78B, 80A, 80B). Each hinge may have a hinge axis (82A, 82B) parallel to a centerline (21) of the turbine. Respective gas flows (36A) are configured by an assembly (60) of the exit pieces to converge on the feed chamber (68) into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.
摘要翻译：一种具有入口喉部（67）的出口件（66），其将来自燃烧器（63）的通道（82）中的燃烧气体流（36A）传导到馈送第一叶片部分（37）的环形室（68）的燃气轮机（26）。出口件还包括形成环形室的周向段的出口部分（69）。出口部分通过铰链（78A，78B，80A，80B）与相邻的出口部分相互连接。每个铰链可以具有平行于涡轮机的中心线（21）的铰链轴线（82A，82B）。相应的气体流（36A）由出口件的组件（60）构成，以将进料腔（68）会聚成均匀的螺旋流，其以最小的周向变化力驱动第一叶片部分。

7. 发明授权

US09476322B2 Combustor transition duct assembly with inner liner 有权
标题翻译：带内衬的燃烧器过渡管道组件
公开(公告)号：US09476322B2
公开(公告)日：2016-10-25
申请号：US13541818
申请日：2012-07-05
申请人： Richard C. Charron , Daniel J. Pierce
发明人： Richard C. Charron , Daniel J. Pierce
IPC分类号： F02C3/00 , F01D25/26 , F01D9/02
CPC分类号： F01D25/26 , F01D9/023 , F05D2250/322 , F05D2250/323 , F05D2250/38 , F05D2250/71
摘要： A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct can be convergent along a majority of the length of the duct when moving from the inlet end to the outlet end thereof. The liner is hollow body with an inner peripheral surface and an outer peripheral surface. The outer peripheral surface of the liner can be correspondingly convergent to the inner peripheral surface of the duct. The inner peripheral surface of the liner can define an internal flow passage through the assembly. Such a construction permits the use of different materials for the liner and the duct and can allow the liner to be readily removed and replaced.
摘要翻译：用于涡轮发动机的过渡管道组件包括具有可拆卸地容纳在其中的内衬管的过渡管道。管道是中空的，具有内周表面和外周表面。管道可以具有入口端和出口端。当从入口端到其出口端移动时，管道的内周表面可以沿着管道的大部分长度会聚。衬套是具有内周面和外周面的中空体。衬套的外周表面可以相应地收敛于管道的内周表面。衬套的内周表面可以限定穿过组件的内部流动通道。这种结构允许使用不同的材料用于衬管和管道，并且可以允许衬垫容易地移除和更换。

8. 发明申请

US20140010644A1 COMBUSTOR TRANSITION DUCT ASSEMBLY WITH INNER LINER 有权
标题翻译：带内胆的COMBUSTOR TRANSITION DUCT装配
公开(公告)号：US20140010644A1
公开(公告)日：2014-01-09
申请号：US13541818
申请日：2012-07-05
申请人： Richard C. Charron , Daniel J. Pierce
发明人： Richard C. Charron , Daniel J. Pierce
IPC分类号： F01D25/26 , F04D29/52
CPC分类号： F01D25/26 , F01D9/023 , F05D2250/322 , F05D2250/323 , F05D2250/38 , F05D2250/71
摘要： A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct can be convergent along a majority of the length of the duct when moving from the inlet end to the outlet end thereof. The liner is hollow body with an inner peripheral surface and an outer peripheral surface. The outer peripheral surface of the liner can be correspondingly convergent to the inner peripheral surface of the duct. The inner peripheral surface of the liner can define an internal flow passage through the assembly. Such a construction permits the use of different materials for the liner and the duct and can allow the liner to be readily removed and replaced.
摘要翻译：用于涡轮发动机的过渡管道组件包括具有可拆卸地容纳在其中的内衬管的过渡管道。管道是中空的，具有内周表面和外周表面。管道可以具有入口端和出口端。当从入口端到其出口端移动时，管道的内周表面可以沿着管道的大部分长度会聚。衬套是具有内周面和外周面的中空体。衬套的外周表面可以相应地收敛于管道的内周表面。衬套的内周表面可以限定穿过组件的内部流动通道。这种结构允许使用不同的材料用于衬管和管道，并且可以允许衬垫容易地移除和更换。

9. 发明申请

US20130139523A1 FULL HOOP CASING FOR MIDFRAME OF INDUSTRIAL GAS TURBINE ENGINE 有权
标题翻译：全工业用于工业燃气轮机发动机
公开(公告)号：US20130139523A1
公开(公告)日：2013-06-06
申请号：US13310855
申请日：2011-12-05
申请人： Gerald A. Myers , Richard C. Charron
发明人： Gerald A. Myers , Richard C. Charron
IPC分类号： F02C3/14 , F23R3/02
CPC分类号： F02C3/14 , F01D25/24 , F01D25/243 , F01D25/285 , F05D2230/70 , F05D2230/72 , F23R3/46
摘要： A can annular industrial gas turbine engine, including: a single-piece rotor shaft spanning a compressor section (82), a combustion section (84), a turbine section (86); and a combustion section casing (10) having a section (28) configured as a full hoop. When the combustion section casing is detached from the engine and moved to a maintenance position to allow access to an interior of the engine, a positioning jig (98) is used to support the compressor section casing (83) and turbine section casing (87).
摘要翻译：一种罐式环形工业燃气涡轮发动机，包括：跨过压缩机部分（82），燃烧部分（84），涡轮部分（86）的单件转子轴; 和具有构成为完全箍的部分（28）的燃烧部分壳体（10）。当燃烧部分壳体与发动机分离并移动到维修位置以允许进入发动机内部时，定位夹具（98）用于支撑压缩机部分壳体（83）和涡轮部分壳体（87）。

10. 发明申请

US20130081399A1 CASING FOR A GAS TURBINE ENGINE 有权
标题翻译：用于燃气涡轮发动机
公开(公告)号：US20130081399A1
公开(公告)日：2013-04-04
申请号：US13252325
申请日：2011-10-04
申请人： David J. Wiebe , David A. Little , Richard C. Charron
发明人： David J. Wiebe , David A. Little , Richard C. Charron
IPC分类号： F02C3/14
CPC分类号： F02C3/14 , F01D9/023 , F23R3/02 , F23R3/46
摘要： A casing for a can annular gas turbine engine, including: a compressed air section (40) spanning between a last row of compressor blades (26) and a first row of turbine blades (28), the compressed air section (40) having a plurality of openings (50) there through, wherein a single combustor/advanced duct assembly (64) extends through each opening (50); and one top hat (68) associated with each opening (50) configured to enclose the associated combustor/advanced duct assembly (64) and seal the opening (50). A volume enclosed by the compressed air section (40) is not greater than a volume of a frustum (54) defined at an upstream end (56) by an inner diameter of the casing at the last row of compressor blades (26) and at a downstream end (60) by an inner diameter of the casing at the first row of turbine blades (28).
摘要翻译：一种用于罐式环形燃气涡轮发动机的壳体，包括：压缩空气部分（40），跨过最后一排压缩机叶片（26）和第一排涡轮叶片（28），压缩空气部分（40）具有多个开口（50）穿过其中，其中单个燃烧器/先进管道组件（64）延伸穿过每个开口（50）; 以及与每个开口（50）相关联的一个顶帽（68），其构造成包围相关联的燃烧器/先进管道组件（64）并密封所述开口（50）。由压缩空气部分（40）包围的体积不大于在上游端（56）处由最后一排压缩机叶片（26）处的壳体的内径限定的平截头体（54）的体积，并且在在第一排涡轮叶片（28）处通过壳体的内径的下游端（60）。

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