公开(公告)号：US5363654A

公开(公告)日：1994-11-15

申请号：US58059

申请日：1993-05-10

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F02C7/18 ,  F23R3/00 ,  F28F13/02 ,  F02C7/12

CPC classification number: F23R3/002 ,  F28F13/02 ,  F05B2260/201 ,  F23R2900/03044 ,  Y02T50/675 ,  Y10S165/908

Abstract: Impingement cooling of a jet engine subassembly, such as a combustor. Adjacent raised corrugation portions and intervening plate portions (having impingement cooling holes) of a corrugated plate define coolant channels in fluid communication with the engine compressor. Dividers positioned transverse to the corrugation portions have a top side attached to a bottom surface of the plate portions and have a bottom side attached to the combustor liner. Corrugation portions define therewithin return channels in fluid communication with post-impingement cooling air. The dividers prevent crossflow between the impingement cooling air and the post-impingement cooling air.

Abstract translation: 喷气发动机组件如燃烧器的冲击冷却。 波纹板的相邻的起皱部分和中间板部分（具有冲击冷却孔）限定与发动机压缩机流体连通的冷却剂通道。 横向于波纹部分定位的分隔件具有附接到板部分的底表面的顶侧，并且具有附接到燃烧器衬套的底侧。 波纹部分限定在与后冲击冷却空气流体连通的返回通道中。 分隔件防止冲击冷却空气和后冲击冷却空气之间的交叉流动。

公开(公告)号：US4901522A

公开(公告)日：1990-02-20

申请号：US281749

申请日：1988-12-09

Applicant: Patrice Commaret ,  Michel A. A. Desaulty ,  Didier H. Hernandez ,  Jean-Claude Laugeois ,  Gerard M. F. Mandet ,  Rodolphe Martinez

Inventor： Patrice Commaret ,  Michel A. A. Desaulty ,  Didier H. Hernandez ,  Jean-Claude Laugeois ,  Gerard M. F. Mandet ,  Rodolphe Martinez

IPC: F23R3/00 ,  F23R3/08

CPC classification number: F23R3/08 ,  F23R3/002 ,  F05B2260/201 ,  F05B2260/202 ,  Y02T50/675

Abstract: The combustion chamber according to the present invention utilizes a double-walled structure only in the converging portion of the combustion chamber. A hot wall is retained adjacent to, but spaced from a corresponding cold wall so as to provide a cooling space between them. An upstream portion of the hot wall is retained in a notch defined by the cold wall, while the downstream portions each have generally radially extending flanges. Studs pass through openings in the adjacent flanges to prevent any relative circumferential movement, while a clamp serves to attach the flanges to the inlet of a turbine. The clamp slidably retains the flanges therein so as to permit relative radial movement to accommodate any thermal expansion and contraction of the combustion chamber, solely by the appended claims.

Abstract translation: 根据本发明的燃烧室仅在燃烧室的会聚部分中使用双壁结构。 热壁与相应的冷壁相邻但间隔开，以便在它们之间提供冷却空间。 热壁的上游部分保持在由冷壁限定的凹口中，而下游部分各自具有大致径向延伸的凸缘。 螺柱穿过相邻凸缘中的开口以防止任何相对的周向运动，而夹具用于将凸缘附接到涡轮机的入口。 夹具可滑动地将凸缘保持在其中，以便仅通过所附权利要求来允许相对径向移动以适应燃烧室的任何热膨胀和收缩。

公开(公告)号：US2654219A

公开(公告)日：1953-10-06

申请号：US24404751

申请日：1951-08-28

Applicant: BBC BROWN BOVERI & CIE

Inventor： TADEUSZ ZABA

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F05B2260/201

公开(公告)号：US12085062B2

公开(公告)日：2024-09-10

申请号：US18451473

申请日：2023-08-17

Applicant: Nordex Energy SE & Co. KG

Inventor： Martin Harich ,  Joachim Nitzpon ,  Florian Adler ,  Moritz Dreher ,  Björn Albertsen

IPC: F03D80/60 ,  F03D7/04 ,  F03D80/70

CPC classification number: F03D80/601 ,  F03D7/04 ,  F03D80/70 ,  F05B2260/201 ,  F05B2270/3032 ,  F05B2270/327

Abstract: A method is for operating a wind turbine. The wind turbine includes a nacelle including a nacelle component, in particular a rotor bearing, and a nacelle air flow influencing unit. The nacelle air flow influencing unit is configured to influence an air flow entering, flowing through and/or exiting the nacelle. The method includes: determining an operating condition of the nacelle component, determining a cooling demand of the nacelle component dependent on the determined operating condition of the nacelle component, controlling an operation of the nacelle air flow influencing unit dependent on the cooling demand of the nacelle component to adapt the air flow to the cooling demand of the nacelle component.

公开(公告)号：US20240060477A1

公开(公告)日：2024-02-22

申请号：US18451473

申请日：2023-08-17

Applicant: Nordex Energy SE & Co. KG

Inventor： Martin Harich ,  Joachim Nitzpon ,  Florian Adler ,  Moritz Dreher ,  Björn Albertsen

IPC: F03D80/60 ,  F03D7/04

CPC classification number: F03D80/601 ,  F03D7/04 ,  F05B2260/201 ,  F05B2270/3032 ,  F05B2270/327

Abstract: A method is for operating a wind turbine. The wind turbine includes a nacelle including a nacelle component, in particular a rotor bearing, and a nacelle air flow influencing unit. The nacelle air flow influencing unit is configured to influence an air flow entering, flowing through and/or exiting the nacelle. The method includes: determining an operating condition of the nacelle component, determining a cooling demand of the nacelle component dependent on the determined operating condition of the nacelle component, controlling an operation of the nacelle air flow influencing unit dependent on the cooling demand of the nacelle component to adapt the air flow to the cooling demand of the nacelle component.

公开(公告)号：US09745852B2

公开(公告)日：2017-08-29

申请号：US14398464

申请日：2013-04-15

Applicant: Siemens Aktiengesellschaft

Inventor： Fathi Ahmad ,  Nihal Kurt

IPC: F01D5/18 ,  F01D5/08 ,  F01D5/30

CPC classification number: F01D5/18 ,  F01D5/082 ,  F01D5/30 ,  F01D5/3015 ,  F05B2260/201 ,  F05D2260/201 ,  Y02T50/676

Abstract: A turbine rotor blade is provided with a blade root, platform adjoining it, and turbine blade on that side of the platform which faces away from the blade root, with at least one opening for feeding coolant into the turbine rotor blade interior on an underside of the blade root, which opening merges into a coolant duct. An axial rotor section for a rotor is provided, having an outer circumferential surface adjoining two end-side first side surfaces with rotor blade holding grooves distributed over the circumference and extending along an axial direction, wherein a turbine rotor blade is arranged in every holding groove, wherein a multiplicity of sealing elements are at the side of a side surface of the rotor section, and lie opposite the end sides of blade roots to form a gap. Multiple outlet holes for impingement cooling of the sealing elements are provided in the end surface.

公开(公告)号：US09359911B2

公开(公告)日：2016-06-07

申请号：US13983477

申请日：2012-02-07

Applicant: Mazyar Abolfazlian ,  Morten Mogensen

Inventor： Mazyar Abolfazlian ,  Morten Mogensen

IPC: F01D5/08 ,  F01D25/12 ,  F03D1/00 ,  F03D11/00 ,  F03D11/04

CPC classification number: F03D9/25 ,  B66C23/207 ,  F01D25/12 ,  F03D13/20 ,  F03D80/00 ,  F03D80/50 ,  F03D80/60 ,  F03D80/80 ,  F03D80/88 ,  F05B2240/14 ,  F05B2240/916 ,  F05B2260/20 ,  F05B2260/201 ,  Y02B10/30 ,  Y02E10/726 ,  Y02E10/728 ,  Y02T50/675

Abstract: A wind turbine for generating electrical energy may include a tower, a nacelle at the top of the tower, and a rotor coupled to a generator within the nacelle. The wind turbine further includes a cooler including a spoiler and at least one cooler panel projecting above a roof of the nacelle. A heliplatform includes a support structure extending from the nacelle and at least partially integrated with the cooler. The wind turbine may also include a crane coupled to the nacelle and configured to move between a first stowed position underneath the nacelle roof and a second operational position. In the operational position, the crane is selectively positionable over the heliplatform. A method of using the wind turbine and crane is also disclosed.

Abstract translation: 用于产生电能的风力涡轮机可以包括塔架，塔顶部的机舱和联接到机舱内的发电机的转子。 风力涡轮机还包括包括扰流器的冷却器和在机舱的顶部上方突出的至少一个冷却器板。 螺旋平台包括从机舱延伸并且至少部分地与冷却器集成的支撑结构。 风力涡轮机还可以包括联接到机舱并被构造成在机舱顶部下方的第一收起位置和第二操作位置之间移动的起重机。 在操作位置，起重机可选择性地定位在螺旋平台上。 还公开了使用风力涡轮机和起重机的方法。

公开(公告)号：US09127551B2

公开(公告)日：2015-09-08

申请号：US13241391

申请日：2011-09-23

Applicant: Andrew R. Narcus ,  Matthew Gent ,  Neal Therrien

Inventor： Andrew R. Narcus ,  Matthew Gent ,  Neal Therrien

IPC: F01D9/02 ,  F23R3/00

CPC classification number: F01D9/023 ,  F05B2250/241 ,  F05B2250/292 ,  F05B2260/201 ,  F05D2250/241 ,  F05D2250/292 ,  F05D2260/201 ,  F23R3/002

Abstract: A scoop (54) over a coolant inlet hole (48) in an outer wall (40B) of a double-walled tubular structure (40A, 40B) of a gas turbine engine component (26, 28). The scoop redirects a coolant flow (37) into the hole. The leading edge (56, 58) of the scoop has a central projection (56) or tongue that overhangs the coolant inlet hole, and a curved undercut (58) on each side of the tongue between the tongue and a generally C-shaped or generally U-shaped attachment base (53) of the scoop. A partial scoop (62) may be cooperatively positioned with the scoop (54).

Abstract translation: 在燃气涡轮发动机部件（26,28）的双壁管状结构（40A，40B）的外壁（40B）中的冷却剂入口孔（48）上方的铲斗（54）。 勺子将冷却剂流（37）重定向到孔中。 勺子的前缘（56,58）具有突出于冷却剂入口孔的中心突起（56）或舌片，以及在舌部的每一侧上的弯曲底切（58），舌部与大致C形或 勺的大致U形附接基座（53）。 部分铲斗（62）可以与铲斗（54）配合地定位。

公开(公告)号：US09093871B2

公开(公告)日：2015-07-28

申请号：US13026057

申请日：2011-02-11

Applicant: Herman Artinian ,  Venkateshwaran Krishnan

Inventor： Herman Artinian ,  Venkateshwaran Krishnan

IPC: F02C6/00 ,  H02K5/124 ,  F04D29/048 ,  F04D29/58 ,  H02K7/09 ,  H02K9/12 ,  F04D13/06 ,  H02K7/14 ,  H02K7/18 ,  H02K9/19

CPC classification number: H02K5/124 ,  F03B3/103 ,  F04D13/0633 ,  F04D13/064 ,  F04D29/048 ,  F04D29/5806 ,  F05B2260/201 ,  H02K7/09 ,  H02K7/14 ,  H02K7/1823 ,  H02K9/12 ,  H02K9/19 ,  H02K2205/03 ,  H02K2213/09 ,  Y02E10/223 ,  Y02T50/675

Abstract: A fluid pumping and energy recovery device may include a housing that defines an impeller chamber and a motor/generator chamber. An impeller may reside within the impeller chamber; and a motor/generator may reside in the motor/generator chamber. The motor/generator may include a stator and a rotor. The rotor may be coupled to the impeller and supported (e.g., by magnetic bearings) to rotate in the stator. The rotor may generate electrical power in a generating mode and rotate in response to electrical power applied to the stator in a motoring mode. Seals may be adapted to hydraulically isolate the pump chamber from the motor/generator chamber by sealing against a rotating surface of the device. In certain instances, sealing is achieved using a bidirectional seal.

Abstract translation: 流体泵送和能量回收装置可以包括限定叶轮室和马达/发电机室的壳体。 叶轮可以驻留在叶轮室内; 并且电动机/发电机可以驻留在电动机/发电机室中。 马达/发电机可以包括定子和转子。 转子可以联接到叶轮并且被支撑（例如通过磁性轴承）以在定子中旋转。 转子可以在发电模式下产生电力并且响应于以电动模式施加到定子的电力而旋转。 密封件可以适于通过密封装置的旋转表面来将泵室与电动机/发电机室液压隔离。 在某些情况下，使用双向密封实现密封。

公开(公告)号：US09052111B2

公开(公告)日：2015-06-09

申请号：US13531132

申请日：2012-06-22

Applicant: Nurhak Erbas-Sen ,  James B. Hoke ,  Albert K. Cheung ,  Robert M. Sonntag ,  Timothy S. Snyder

Inventor： Nurhak Erbas-Sen ,  James B. Hoke ,  Albert K. Cheung ,  Robert M. Sonntag ,  Timothy S. Snyder

IPC: F23R3/00 ,  F23R3/06 ,  F23R3/04 ,  F23R3/10 ,  F23R3/50

CPC classification number: F23R3/06 ,  F05B2260/201 ,  F05B2260/202 ,  F23R3/002 ,  F23R3/04 ,  F23R3/10 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03044

Abstract: A turbine engine combustor wall includes support shell and a heat shield. The support shell includes shell quench apertures, first impingement apertures, and second impingement apertures. The combustor heat shield includes shield quench apertures fluidly coupled with the shell quench apertures, first effusion apertures fluidly coupled with the first impingement apertures, and second effusion apertures fluidly coupled with the second impingement apertures. The shield quench apertures and the first effusion apertures are configured in a first axial region of the heat shield, and the second effusion apertures are configured in a second axial region of the heat shield located axially between the first axial region and a downstream end of the heat shield. A density of the first effusion apertures in the first axial region is greater than a density of the second effusion apertures in the second axial region.

Abstract translation: 涡轮发动机燃烧器壁包括支撑壳和隔热罩。 支撑壳包括壳体淬火孔，第一冲击孔和第二冲击孔。 燃烧器热屏蔽包括与壳体骤冷孔流体耦合的屏蔽骤冷孔，与第一冲击孔流体连接的第一渗出孔以及与第二冲击孔流体连接的第二渗出孔。 所述屏蔽骤冷孔和所述第一渗出孔构造在所述隔热罩的第一轴向区域中，并且所述第二渗出孔构造在所述隔热罩的第二轴向区域中，所述第二轴向区域轴向位于所述第一轴向区域和所述第一轴向区域的下游端之间 隔热板。 在第一轴向区域中的第一渗出孔的密度大于第二轴向区域中的第二渗出孔的密度。