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1. 发明授权

US06773231B2 Turbine blade core cooling apparatus and method of fabrication 有权
标题翻译：涡轮叶片芯冷却装置及其制造方法
公开(公告)号：US06773231B2
公开(公告)日：2004-08-10
申请号：US10162755
申请日：2002-06-06
申请人： Ronald Scott Bunker , Frederic Joseph Klug , Shyh-Chin Huang , Susan Marie Hyde , Nirm Velumylum Nirmalan
发明人： Ronald Scott Bunker , Frederic Joseph Klug , Shyh-Chin Huang , Susan Marie Hyde , Nirm Velumylum Nirmalan
IPC分类号： F01D518
CPC分类号： F01D5/225 , B22C9/04 , B22C9/10 , F01D5/187 , F05D2260/22141 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： The present invention provides a cooling apparatus for cooling a turbine blade. The cooling apparatus comprises a pressure side plate comprising a plurality of pressure ribs, a suction side plate comprising a plurality of suction ribs, and a plurality of flow redirection areas. The pressure side plate is disposed over the suction side plate, where the pressure ribs are disposed at a first angle with respect to a blade span reference line and the suction ribs are disposed at a second angle with respect to the blade span reference line, to form the flow redirection areas. The present invention provides a method of fabricating the cooling apparatus for the turbine blade comprising aligning the pressure side plate and the suction side plate to form the plurality of flow redirection areas between the pressure side plate and the suction side plate.
摘要翻译：本发明提供一种用于冷却涡轮叶片的冷却装置。冷却装置包括压力侧板，其包括多个加压肋，包括多个吸入肋的吸力侧板和多个流动重定向区域。压力侧板设置在吸力侧板上方，其中压力肋相对于叶片跨度基准线以第一角度设置，并且抽吸肋相对于叶片跨距参考线设置成第二角度，形成流重定向区域。本发明提供一种制造涡轮叶片的冷却装置的方法，包括使压力侧板和吸力侧板对准，以在压力侧板和吸力侧板之间形成多个流动重定向区域。

2. 发明授权

US06464461B2 Steam cooling system for a gas turbine 失效
标题翻译：燃气轮机的蒸汽冷却系统
公开(公告)号：US06464461B2
公开(公告)日：2002-10-15
申请号：US09731982
申请日：2000-12-08
申请人： Ian David Wilson , Kevin Joseph Barb , Ming Cheng Li , Susan Marie Hyde , Thomas Charles Mashey , Ronald Richard Wesorick , Christopher Charles Glynn , Martin C. Hemsworth
发明人： Ian David Wilson , Kevin Joseph Barb , Ming Cheng Li , Susan Marie Hyde , Thomas Charles Mashey , Ronald Richard Wesorick , Christopher Charles Glynn , Martin C. Hemsworth
IPC分类号： F01D508
CPC分类号： F01D5/085 , F02C7/16 , F05D2260/2322 , Y02T50/676
摘要： The steam cooling circuit for a gas turbine includes a bore tube assembly supplying steam to circumferentially spaced radial tubes coupled to supply elbows for transitioning the radial steam flow in an axial direction along steam supply tubes adjacent the rim of the rotor. The supply tubes supply steam to circumferentially spaced manifold segments located on the aft side of the 1-2 spacer for supplying steam to the buckets of the first and second stages. Spent return steam from these buckets flows to a plurality of circumferentially spaced return manifold segments disposed on the forward face of the 1-2 spacer. Crossover tubes couple the steam supply from the steam supply manifold segments through the 1-2 spacer to the buckets of the first stage. Crossover tubes through the 1-2 spacer also return steam from the buckets of the second stage to the return manifold segments. Axially extending return tubes convey spent cooling steam from the return manifold segments to radial tubes via return elbows.
摘要翻译：用于燃气涡轮机的蒸汽冷却回路包括孔管组件，其将周向间隔开的径向管供给蒸汽，所述径向管连接到供应弯头，以沿着与沿转子边缘的蒸汽供应管沿轴向方向转换径向蒸汽流。供应管将位于1-2间隔物的后侧的周向隔开的歧管段供应蒸汽，以将蒸汽供应到第一和第二级的桶。来自这些铲斗的废水返回蒸汽流向设置在1-2间隔物的前表面上的多个周向间隔开的返回歧管段。交叉管将来自蒸汽供应歧管段的蒸汽供应通过1-2间隔件连接到第一级的桶。通过1-2间隔物的交叉管还将蒸汽从第二级的桶返回到回流歧管段。轴向延伸的回流管通过返回弯头将废冷却蒸汽从返回歧管段传送到径向管。

3. 发明授权

US06910868B2 Airfoil shape for a turbine bucket 有权
标题翻译：涡轮叶片的翼型
公开(公告)号：US06910868B2
公开(公告)日：2005-06-28
申请号：US10624632
申请日：2003-07-23
申请人： Susan Marie Hyde , Robert Romany By , Judd Dodge Tressler , Jon Conrad Schaeffer , Calvin Levy Sims
发明人： Susan Marie Hyde , Robert Romany By , Judd Dodge Tressler , Jon Conrad Schaeffer , Calvin Levy Sims
IPC分类号： F01D5/14 , F01D5/20 , F03B11/00
CPC分类号： F01D5/141 , F01D5/225 , F05D2250/70 , F05D2250/74 , Y10S416/02
摘要： Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 0.938 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.150 inches in directions normal to the surface of the airfoil.
摘要翻译：第三级涡轮机叶片具有基本上符合X，Y和Z的笛卡尔坐标值的机翼型材，其中X和Y值为英寸，Z值为从0到0.938可转换为Z距离的无量纲值将Z值乘以翼型件的高度（英寸）。 X和Y值是通过平滑连续弧连接时定义每个距离Z处的翼型轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的翼型形状。作为相同常数或数字的函数，X和Y距离可以是可缩放的，以提供用于铲斗的放大或缩小的翼型部分。由X，Y和Z距离给出的额定翼型在垂直于翼面表面的方向上在±0.150英寸的范围内。

4. 发明授权

US06884038B2 Airfoil shape for a turbine bucket 失效
标题翻译：涡轮叶片的翼型
公开(公告)号：US06884038B2
公开(公告)日：2005-04-26
申请号：US10621460
申请日：2003-07-18
申请人： Susan Marie Hyde , Robert Romany By , Jon Conrad Schaeffer , Calvin Levy Sims , Michael Ernest Boisclair
发明人： Susan Marie Hyde , Robert Romany By , Jon Conrad Schaeffer , Calvin Levy Sims , Michael Ernest Boisclair
IPC分类号： F01D5/18 , F01D5/00 , F01D5/14
CPC分类号： F01D5/141 , F05D2250/00 , Y10S416/02
摘要： Fourth stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.150 inches in directions normal to the surface of the airfoil.
摘要翻译：第四级涡轮机叶片具有基本上符合X，Y和Z的笛卡尔坐标值的翼型轮廓，其中X和Y值以英寸计，Z值是从0到1可转换成Z距离的无量纲值将Z值乘以翼型件的高度（英寸）。 X和Y值是通过平滑连续弧连接时定义每个距离Z处的翼型轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的翼型形状。作为相同常数或数字的函数，X和Y距离可以是可缩放的，以提供用于铲斗的放大或缩小的翼型部分。由X，Y和Z距离给出的标称翼型在垂直于翼面表面的方向上在±0.150英寸的范围内。

5. 发明授权

US06499742B1 Brush seal assembly and method of using brush seal assembly 有权
标题翻译：刷子密封组件及其使用方法
公开(公告)号：US06499742B1
公开(公告)日：2002-12-31
申请号：US09682322
申请日：2001-08-20
申请人： Ming Zhou , Sal Albert Leone , Susan Marie Hyde
发明人： Ming Zhou , Sal Albert Leone , Susan Marie Hyde
IPC分类号： F16J15453
CPC分类号： F16J15/445 , F16J15/002 , F16J15/3288
摘要： The invention provides a brush seal assembly, and method of using, for reducing adverse fluid flow effects to a brush seal,.the brush seal assembly comprising a support housing having a passage; a rotating shaft disposed in the passage of the support housing, the rotating shaft including a shaft body having a periphery and an annular tooth extending around the periphery of the shaft body; and an annular brush seal including a plurality of bristles extending around the shaft body, each of the plurality of bristles attached to and extending from the support housing in the passage towards the rotating shaft. The brush seal assembly further includes an annular abradable material portion being constructed of an abradable material, the abradable material portion having a groove extending around an inner periphery thereof, the abradable material portion disposed in the passage around, and proximate to, the tooth of the rotating shaft such that the tooth of the rotating shaft is disposed in the groove of the abradable material portion.
摘要翻译：本发明提供一种刷子密封组件，以及用于减少对刷子密封件的不利流体流动影响的方法。该刷子密封组件包括具有通道的支撑壳体; 旋转轴，设置在所述支撑壳体的通道中，所述旋转轴包括具有周边的轴体和围绕所述轴体的周边延伸的环形齿; 以及环形刷密封，其包括围绕所述轴体延伸的多个刷毛，所述多个刷毛中的每一个附着到所述通道中的所述支撑壳体中并且从所述旋转轴延伸。刷密封组件还包括由可磨损材料构成的环形耐磨材料部分，所述可磨损材料部分具有围绕其内周延伸的凹槽，所述可磨损材料部分设置在所述通道内，旋转轴，使得旋转轴的齿设置在可磨损材料部分的凹槽中。

6. 发明授权

US06402157B1 Brush seal and method of using brush seal 有权
标题翻译：刷子密封和使用刷子密封的方法
公开(公告)号：US06402157B1
公开(公告)日：2002-06-11
申请号：US09682325
申请日：2001-08-20
申请人： Ming Zhou , Sal Albert Leone , Susan Marie Hyde , Bruce Miller , Peter A. Stinnett
发明人： Ming Zhou , Sal Albert Leone , Susan Marie Hyde , Bruce Miller , Peter A. Stinnett
IPC分类号： F16J1544
CPC分类号： F16J15/3288
摘要： The invention provides a brush seal, and a method of using a brush seal, for providing a seal between a support housing and a rotating shaft. The brush seal comprises a support portion; a back plate connected to and extending from the support portion on a back side of the support portion. The brush seal further includes a set of bristles attached to the support portion, the back plate disposed on a back side of the set of bristles and supporting the set of bristles. The brush seal further includes at least one fitting portion connected to and extending from the support portion, each of the at least one fitting portions configured to mate with a corresponding slot in the support housing so as to prevent mis-fit of the brush seal in the support housing.
摘要翻译：本发明提供一种刷子密封件，以及使用刷子密封件的方法，用于在支撑壳体和旋转轴之间提供密封。刷密封包括支撑部分; 连接到所述支撑部分的背侧上的支撑部分并从所述支撑部分延伸的背板。刷子密封件还包括附接到支撑部分的一组刷毛，背板设置在该组刷毛的后侧并支撑该组刷毛。刷子密封件还包括连接到支撑部分并且从支撑部分延伸的至少一个装配部分，所述至少一个装配部分中的每一个配置成与支撑壳体中的相应狭槽配合，以防止刷密封件的错配支撑住房。

7. 发明授权

US06957949B2 Internal cooling circuit for gas turbine bucket 有权
标题翻译：燃气轮机内部冷却回路
公开(公告)号：US06957949B2
公开(公告)日：2005-10-25
申请号：US09777998
申请日：2001-02-07
申请人： Susan Marie Hyde , Richard Mallory Davis
发明人： Susan Marie Hyde , Richard Mallory Davis
IPC分类号： F02C7/16 , F01D5/18 , B63H1/14
CPC分类号： F01D5/187
摘要： In a gas turbine bucket having a shank portion and an airfoil portion having leading and trailing edges and pressure and suction sides, an internal cooling circuit, the internal cooling circuit having a serpentine configuration including plural radial outflow passages and plural radial inflow passages, and wherein a coolant inlet passage communicates with a first of the radial outflow passages along the trailing edge, the first radial outflow passage having a plurality of radially extending and radially spaced elongated rib segments extending between and connecting the pressure and suction sides in a middle region of the first passage to prevent ballooning of the pressure and suction sides at the first radial outflow passage.
摘要翻译：在具有柄部和具有前缘和后缘以及压力和吸力侧的翼型部的燃气轮机桶中，内部冷却回路具有包括多个径向流出通道和多个径向流入通道的蛇形结构，冷却剂入口通道沿着后缘与第一径向流出通道连通，第一径向流出通道具有多个径向延伸且径向间隔开的细长肋段，该细长肋段在第二径向流出通道的中间区域之间延伸并连接在压力和吸力侧第一通道，以防止第一径向流出通道处的压力和吸力侧膨胀。

8. 发明授权

US06450770B1 Second-stage turbine bucket airfoil 失效
标题翻译：二级涡轮机叶翼
公开(公告)号：US06450770B1
公开(公告)日：2002-09-17
申请号：US09892911
申请日：2001-06-28
申请人： John Zhiqiang Wang , Robert Romany By , Calvin L. Sims , Susan Marie Hyde
发明人： John Zhiqiang Wang , Robert Romany By , Calvin L. Sims , Susan Marie Hyde
IPC分类号： F01D514
CPC分类号： F01D5/141 , F05D2240/301 , Y10S416/02
摘要： The second-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X and Y values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket. The second-stage wheel has sixty buckets.
摘要翻译：第二级铲斗具有基本上符合表I中以英寸表示的X，Y和Z的笛卡尔坐标值的翼型，其中Z是垂直于涡轮中心线半径的平面的垂直距离，并且包含X和 Y值，Z值在翼型的径向最内部气动部分的X，Y平面处从零开始，X和Y是在每个距离Z处限定翼型轮廓的坐标值.X和Y值可以缩放为相同常数或数字的功能为铲斗提供放大或缩小的翼型部分。第二级车轮有六十个铲斗。

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