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1. 发明授权

US07153090B2 System and method for passive load attenuation in a wind turbine 有权
标题翻译：风力发电机中被动负载衰减的系统和方法
公开(公告)号：US07153090B2
公开(公告)日：2006-12-26
申请号：US11015259
申请日：2004-12-17
申请人： Guy Wayne DeLeonardo , Scott Roger Finn , Peter Michael Finnigan , Donald Joseph Kasperski
发明人： Guy Wayne DeLeonardo , Scott Roger Finn , Peter Michael Finnigan , Donald Joseph Kasperski
IPC分类号： F03B15/06
CPC分类号： F03D1/0675 , F05B2240/30 , F05B2240/301 , Y02E10/721
摘要： In accordance with certain embodiments, a wind turbine blade includes an outer skin and an internal support structure. The skin has a closed airfoil shape and includes an outer surface, an inner surface, and opposite sides along a length of the blade. The internal support structure is disposed within the closed airfoil shape. The internal support structure includes at least one shear load bearing member disposed across the opposite sides and oriented lengthwise along the length of the blade. The internal support structure further includes a plurality of bending load bearing members disposed along the inner surface in a lengthwise direction along the length of the blade. The internal support structure is configured to position a shear center and a center of aerodynamic pressure loading of the blade at different locations relative to one another.
摘要翻译：根据某些实施例，风力涡轮机叶片包括外部皮肤和内部支撑结构。皮肤具有封闭的翼型形状并且包括外表面，内表面和沿刀片的长度的相对侧。内部支撑结构设置在封闭的翼型形状内。内部支撑结构包括横跨相对侧设置并沿着叶片的长度沿纵向定向的至少一个剪切载荷承载构件。内部支撑结构还包括多个沿刀片的长度方向沿长度方向沿内表面设置的弯曲载荷承载部件。内部支撑结构构造成将叶片的剪切中心和空气动力学压力的中心相对于彼此定位在不同的位置。

2. 发明申请

US20100183436A1 DISCRETE LOAD FINS FOR INDIVIDUAL STATOR VANES 有权
标题翻译：用于个体定位器的离散负载FINS
公开(公告)号：US20100183436A1
公开(公告)日：2010-07-22
申请号：US12356786
申请日：2009-01-21
申请人： Donald Joseph Kasperski
发明人： Donald Joseph Kasperski
IPC分类号： F01D25/24
CPC分类号： F01D9/042 , F01D9/04 , F01D9/041 , F01D25/24 , F01D25/246 , F01D25/26 , F04D29/542 , Y02T50/673
摘要： An exemplary embodiment of the invention is directed to a turbine engine having a circumferential casing with a circumferentially extending slot formed in an inner wall. A radially inwardly facing fin-ring is disposed in the slot and has a radially inwardly projecting fin extending axially there across. A radially inwardly extending stator blade has a base and an airfoil. The base is disposed in the casing slot, radially inwardly of the fin-ring. A complementary base slot is disposed in the stator blade base and is configured to receive the fin therein for the transfer of a circumferential force, applied to the stator blade, to the fin-ring.
摘要翻译：本发明的示例性实施例涉及一种涡轮发动机，其具有周向壳体，其具有形成在内壁中的周向延伸的槽。径向向内的翅片环设置在槽中并且具有沿着轴向延伸的径向向内突出的翅片。径向向内延伸的定子叶片具有基部和翼型。底座设置在翅片环的径向内侧的套管槽中。互补的基座槽设置在定子叶片基座中并且构造成在其中容纳翅片以便将施加到定子叶片的周向力传递到翅片环。

3. 发明授权

US08133019B2 Discrete load fins for individual stator vanes 有权
标题翻译：用于各个定子叶片的离散负载散热片
公开(公告)号：US08133019B2
公开(公告)日：2012-03-13
申请号：US12356786
申请日：2009-01-21
申请人： Donald Joseph Kasperski
发明人： Donald Joseph Kasperski
IPC分类号： F03B1/00
CPC分类号： F01D9/042 , F01D9/04 , F01D9/041 , F01D25/24 , F01D25/246 , F01D25/26 , F04D29/542 , Y02T50/673
摘要： An exemplary embodiment of the invention is directed to a turbine engine having a circumferential casing with a circumferentially extending slot formed in an inner wall. A radially inwardly facing fin-ring is disposed in the slot and has a radially inwardly projecting fin extending axially there across. A radially inwardly extending stator blade has a base and an airfoil. The base is disposed in the casing slot, radially inwardly of the fin-ring. A complementary base slot is disposed in the stator blade base and is configured to receive the fin therein for the transfer of a circumferential force, applied to the stator blade, to the fin-ring.
摘要翻译：本发明的示例性实施例涉及一种涡轮发动机，其具有周向壳体，其具有形成在内壁中的周向延伸的槽。径向向内的翅片环设置在槽中并且具有沿着轴向延伸的径向向内突出的翅片。径向向内延伸的定子叶片具有基部和翼型。底座设置在翅片环的径向内侧的套管槽中。互补的基座槽设置在定子叶片基座中并且构造成在其中容纳翅片以便将施加到定子叶片的周向力传递到翅片环。

4. 发明申请

US20120051927A1 AIRFOIL SHAPE FOR COMPRESSOR INLET GUIDE VANE 有权
标题翻译：压缩机入口导向板的气翼形状
公开(公告)号：US20120051927A1
公开(公告)日：2012-03-01
申请号：US12872160
申请日：2010-08-31
申请人： Christopher Edward LaMaster , Venkata Siva P. Chaluvadi , Donald Joseph Kasperski
发明人： Christopher Edward LaMaster , Venkata Siva P. Chaluvadi , Donald Joseph Kasperski
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D9/02 , F04D29/563 , F05D2250/74 , Y10S416/05
摘要： An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete inlet guide vane airfoil shape.
摘要翻译：具有基本上符合表A所示的X，Y和Z的笛卡尔坐标值的公称轮廓的制品.X和Y是以平滑连续的弧连接时以每英寸限定翼型轮廓部分的距离，以英寸为单位 Z英寸。 Z距离处的轮廓部分可以彼此平滑地连接以形成完整的入口导叶翼型。

5. 发明申请

US20100329872A1 METHOD AND APPARATUS FOR ASSEMBLING ROTATING MACHINES 有权
标题翻译：组装旋转机械的方法和装置
公开(公告)号：US20100329872A1
公开(公告)日：2010-12-30
申请号：US12494764
申请日：2009-06-30
申请人： Donald Joseph Kasperski
发明人： Donald Joseph Kasperski
IPC分类号： F01D5/30 , B23P11/00
CPC分类号： F01D5/3007 , F05D2230/60 , Y10T29/49236 , Y10T29/49245 , Y10T29/49321 , Y10T29/49336
摘要： A method for assembling a rotating machine includes providing a rotating element. The method also includes forming a first dovetail slot having a first axial length within a portion of a rotating element. The first dovetail slot is substantially parallel to an axial centerline of the rotating element. The method further includes forming a second dovetail slot having a second axial length within a portion of the rotating element. The second dovetail slot is substantially parallel to the axial centerline of the rotating element. At least a portion of the second dovetail slot is radially outboard of at least a portion of the first dovetail slot. The first axial length is greater than the second axial length. The method also includes enclosing at least a portion of the rotating element within at least a portion of a casing.
摘要翻译：一种组装旋转机器的方法包括提供旋转元件。该方法还包括在旋转元件的一部分内形成具有第一轴向长度的第一燕尾槽。第一燕尾槽基本上平行于旋转元件的轴向中心线。该方法还包括在旋转元件的一部分内形成具有第二轴向长度的第二燕尾槽。第二燕尾槽基本上平行于旋转元件的轴向中心线。第二燕尾槽的至少一部分在第一燕尾槽的至少一部分的径向外侧。第一轴向长度大于第二轴向长度。该方法还包括在壳体的至少一部分内包围旋转元件的至少一部分。

6. 发明授权

US08491260B2 Airfoil shape for a compressor vane 有权
标题翻译：用于压缩机叶片的翼型
公开(公告)号：US08491260B2
公开(公告)日：2013-07-23
申请号：US12872148
申请日：2010-08-31
申请人： Michael James Dutka , Donald Joseph Kasperski
发明人： Michael James Dutka , Donald Joseph Kasperski
IPC分类号： F01D9/02
CPC分类号： F01D5/141 , F05D2250/74
摘要： An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.
摘要翻译：具有基本上符合表A所示的X，Y和Z的笛卡尔坐标值的公称轮廓的制品.X和Y是以平滑连续的弧连接时以每英寸限定翼型轮廓部分的距离，以英寸为单位 Z英寸。 Z距离处的轮廓部分可以彼此平滑地连接以形成完整的翼型形状。

7. 发明授权

US08251668B2 Method and apparatus for assembling rotating machines 有权
标题翻译：用于组装旋转机器的方法和装置
公开(公告)号：US08251668B2
公开(公告)日：2012-08-28
申请号：US12494764
申请日：2009-06-30
申请人： Donald Joseph Kasperski
发明人： Donald Joseph Kasperski
IPC分类号： F01D5/30 , F04D29/34
CPC分类号： F01D5/3007 , F05D2230/60 , Y10T29/49236 , Y10T29/49245 , Y10T29/49321 , Y10T29/49336
摘要： A method for assembling a rotating machine and a blade attachment mechanism are provided. A first dovetail slot having a first axial length and a second dovetail slot having a second axial length are each formed in the attachment mechanism such that the second dovetail slot is radially outboard of the first dovetail slot. First axial length is greater than the second axial length and each slot is substantially parallel to an axial centerline of the rotating machine. A first dovetail lobe having a third axial length that is shorter than the first axial length and a second dovetail lobe having a fourth axial length, shorter than the first axial length and longer than the third axial length, are each formed in the attachment mechanism and positioned to correspond with first and second dovetail slot, respectively, such that the second dovetail lobe is radially outward from the first dovetail lobe.
摘要翻译：提供了一种用于组装旋转机器和刀片附接机构的方法。具有第一轴向长度的第一燕尾槽和具有第二轴向长度的第二燕尾槽各自形成在附接机构中，使得第二燕尾槽在第一燕尾槽的径向外侧。第一轴向长度大于第二轴向长度，并且每个槽基本上平行于旋转机器的轴向中心线。具有比第一轴向长度短的第三轴向长度的第一燕尾形叶片和具有比第一轴向长度短并且长于第三轴向长度的第四轴向长度的第二燕尾形叶片分别形成在附接机构中，定位成分别对应于第一和第二燕尾槽，使得第二燕尾形叶片从第一燕尾形叶片径向向外。

8. 发明授权

US08186963B2 Airfoil shape for compressor inlet guide vane 有权
标题翻译：用于压缩机入口导叶的翼型
公开(公告)号：US08186963B2
公开(公告)日：2012-05-29
申请号：US12872160
申请日：2010-08-31
申请人： Christopher Edward LaMaster , Venkata Siva P. Chaluvadi , Donald Joseph Kasperski
发明人： Christopher Edward LaMaster , Venkata Siva P. Chaluvadi , Donald Joseph Kasperski
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D9/02 , F04D29/563 , F05D2250/74 , Y10S416/05
摘要： An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete inlet guide vane airfoil shape.
摘要翻译：具有基本上符合表A所示的X，Y和Z的笛卡尔坐标值的公称轮廓的制品.X和Y是以平滑连续的弧连接时以每英寸限定翼型轮廓部分的距离，以英寸为单位 Z英寸。 Z距离处的轮廓部分可以彼此平滑地连接以形成完整的入口导叶翼型。

9. 发明授权

US08047778B2 Method and apparatus for insuring proper installation of stators in a compressor case 有权
标题翻译：确保在压缩机壳体中正确安装定子的方法和装置
公开(公告)号：US08047778B2
公开(公告)日：2011-11-01
申请号：US12349270
申请日：2009-01-06
申请人： Donald Joseph Kasperski , Dwight Eric Davidson
发明人： Donald Joseph Kasperski , Dwight Eric Davidson
IPC分类号： F01D9/04
CPC分类号： F01D25/24 , F01D9/04 , F01D9/042 , F01D25/246 , F04D29/526 , F04D29/542 , F04D29/644 , Y10T29/49323
摘要： Disclosed herein is a compressor case assembly that includes a compressor case section having an assembly track and a set of stator portions that are insertable in the assembly track, the compressor case section and the set of stator portions are configured such that the set of stator portions only assembles to the compressor case section in a single configuration.
摘要翻译：本文公开了一种压缩机壳体组件，其包括压缩机壳体部分，该压缩机壳体部分具有可组装轨道的组合轨道和可插入到组装轨迹中的一组定子部分，压缩机壳体部分和该组定子部分被构造成使得该组定子部分仅在单个配置中组装到压缩机壳体部分。

10. 发明申请

US20120051926A1 AIRFOIL SHAPE FOR A COMPRESSOR VANE 有权
标题翻译：压缩机VANE的气翼形状
公开(公告)号：US20120051926A1
公开(公告)日：2012-03-01
申请号：US12872148
申请日：2010-08-31
申请人： Michael James Dutka , Donald Joseph Kasperski
发明人： Michael James Dutka , Donald Joseph Kasperski
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2250/74
摘要： An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.
摘要翻译：具有基本上符合表A所示的X，Y和Z的笛卡尔坐标值的公称轮廓的制品.X和Y是以平滑连续的弧连接时以每英寸限定翼型轮廓部分的距离，以英寸为单位 Z英寸。 Z距离处的轮廓部分可以彼此平滑地连接以形成完整的翼型形状。

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