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1. 发明授权

US08511978B2 Airfoil array with an endwall depression and components of the array 有权
标题翻译：翼型阵列具有端壁凹陷和阵列的部件
公开(公告)号：US08511978B2
公开(公告)日：2013-08-20
申请号：US11415898
申请日：2006-05-02
申请人： Eunice Allen-Bradley , Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
发明人： Eunice Allen-Bradley , Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
IPC分类号： F01D1/04 , F01D9/02
CPC分类号： F01D5/145 , F01D5/143 , F01D9/041 , F05D2240/80 , F05D2250/291 , F05D2250/60
摘要： An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28 or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages 74. The endwall has a trough 100 toward a pressure side of the passage and a more elevated profile toward a suction side of the passage for reducing secondary flow losses.
摘要翻译：翼型阵列包括横向延伸的端壁56，其具有从端壁突出的一系列诸如28或38的翼型件。翼型件与端壁协作以限定一系列流体流动通道74.端壁具有朝向通道的压力侧的槽100和朝向通道的吸入侧的更加升高的型面，用于减少二次流动损失。

2. 发明授权

US09382807B2 Non-axisymmetric rim cavity features to improve sealing efficiencies 有权
标题翻译：非轴对称轮辋腔特征，以提高密封效率
公开(公告)号：US09382807B2
公开(公告)日：2016-07-05
申请号：US13466254
申请日：2012-05-08
申请人： Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
发明人： Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
IPC分类号： F01D11/02 , F01D11/00 , F01D5/08
CPC分类号： F01D11/001 , F01D5/081 , F01D11/02 , F05D2250/73 , F05D2260/97
摘要： Turbomachinery, such as a gas turbine engine, has parts with opposed first and second surfaces and with a cavity between the surfaces and with the first surface moving relative to the second surface. The turbomachinery further has at least one feature for creating pressure variations incorporated into the first and second surfaces.
摘要翻译：涡轮机械，例如燃气涡轮发动机，具有相对的第一和第二表面的部件，并且在表面之间具有空腔，并且第一表面相对于第二表面移动。涡轮机械还具有用于产生并入第一和第二表面的压力变化的至少一个特征。

3. 发明授权

US07887297B2 Airfoil array with an endwall protrusion and components of the array 有权
标题翻译：翼型阵列具有端壁突起和阵列的部件
公开(公告)号：US07887297B2
公开(公告)日：2011-02-15
申请号：US11415915
申请日：2006-05-02
申请人： Eunice Allen-Bradley , Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
发明人： Eunice Allen-Bradley , Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
IPC分类号： F01D5/22
CPC分类号： F01D5/145 , F01D5/143 , F01D9/041 , F05D2240/121 , F05D2240/303 , F05D2240/90 , F05D2250/291 , F05D2250/60
摘要： An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28, or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages 74. The endwall has a hump 84 toward a pressure side of the passage and a less elevated profile toward a suction side of the passage for reducing secondary flow losses.
摘要翻译：翼型阵列包括横向延伸的端壁56，其具有从端壁突出的一系列诸如28或38的翼型件。翼型件与端壁协作以限定一系列流体流动通道74.端壁具有朝向通道的压力侧的隆起部84，并且朝向通道的吸入侧的较小的升高的型面减少二次流动损失。

4. 发明申请

US20130302136A1 NON-AXISYMMETRIC RIM CAVITY FEATURES TO IMPROVE SEALING EFFICIENCIES 有权
标题翻译：提高密封效率的非轴对称RIM CAVITY特性
公开(公告)号：US20130302136A1
公开(公告)日：2013-11-14
申请号：US13466254
申请日：2012-05-08
申请人： Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
发明人： Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
IPC分类号： F01D11/08
CPC分类号： F01D11/001 , F01D5/081 , F01D11/02 , F05D2250/73 , F05D2260/97
摘要： Turbomachinery, such as a gas turbine engine, has parts with opposed first and second surfaces and with a cavity between the surfaces and with the first surface moving relative to the second surface. The turbomachinery further has at least one feature for creating pressure variations incorporated into the first and second surfaces.
摘要翻译：涡轮机械，例如燃气涡轮发动机，具有相对的第一和第二表面的部件，并且在表面之间具有空腔，并且第一表面相对于第二表面移动。涡轮机械还具有用于产生并入第一和第二表面的压力变化的至少一个特征。

5. 发明申请

US20110243749A1 GAS TURBINE ENGINE WITH NON-AXISYMMETRIC SURFACE CONTOURED ROTOR BLADE PLATFORM 有权
标题翻译：具有非轴对称表面轮廓转子叶片平台的气体涡轮发动机
公开(公告)号：US20110243749A1
公开(公告)日：2011-10-06
申请号：US12753211
申请日：2010-04-02
申请人： Thomas J. Praisner , Eric A. Grover
发明人： Thomas J. Praisner , Eric A. Grover
IPC分类号： F01D5/14
CPC分类号： F01D11/00 , F01D5/143 , F01D5/225 , F05D2240/80 , F05D2250/61 , Y02T50/673
摘要： A rotor blade for a gas turbine engine includes a platform section between a root section and an airfoil section, the platform section having a non-axisymmetric surface contour.
摘要翻译：用于燃气涡轮发动机的转子叶片包括在根部和翼型部之间的平台部分，平台部具有非轴对称的表面轮廓。

6. 发明授权

US09976433B2 Gas turbine engine with non-axisymmetric surface contoured rotor blade platform 有权
公开(公告)号：US09976433B2
公开(公告)日：2018-05-22
申请号：US12753211
申请日：2010-04-02
申请人： Thomas J. Praisner , Eric A. Grover
发明人： Thomas J. Praisner , Eric A. Grover
IPC分类号： F01D11/00 , F01D5/14 , F01D5/22
CPC分类号： F01D11/00 , F01D5/143 , F01D5/225 , F05D2240/80 , F05D2250/61 , Y02T50/673
摘要： A rotor blade for a gas turbine engine includes a platform section between a root section and an airfoil section, the platform section having a non-axisymmetric surface contour.

7. 发明申请

US20110236200A1 GAS TURBINE ENGINE WITH NON-AXISYMMETRIC SURFACE CONTOURED VANE PLATFORM 有权
标题翻译：具有非轴对称表面轮廓平面的气体涡轮发动机
公开(公告)号：US20110236200A1
公开(公告)日：2011-09-29
申请号：US12730191
申请日：2010-03-23
申请人： Eric A. Grover , Thomas J. Praisner
发明人： Eric A. Grover , Thomas J. Praisner
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F01D5/143 , F01D9/047 , F05D2240/128 , F05D2240/80 , F05D2250/71 , Y02T50/673
摘要： A vane segment for a gas turbine engine according to an exemplary aspect of the present disclosure includes an inner vane platform relative an axis, the inner vane platform having a non-axisymmetric surface contour.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的叶片段包括相对于轴线的内叶片平台，所述内叶片平台具有非轴对称表面轮廓。

8. 发明申请

US20100254797A1 ENDWALL WITH LEADING-EDGE HUMP 有权
标题翻译：终极前卫
公开(公告)号：US20100254797A1
公开(公告)日：2010-10-07
申请号：US12418647
申请日：2009-04-06
申请人： Eric A. Grover , Thomas J. Praisner , Noel Modesto-Madera , Renee J. Jurek
发明人： Eric A. Grover , Thomas J. Praisner , Noel Modesto-Madera , Renee J. Jurek
IPC分类号： F01D9/04 , F01D5/14
CPC分类号： F01D5/143 , F05D2240/121 , F05D2240/303 , F05D2250/711
摘要： An example airfoil assembly includes a base having an airfoil projecting radially therefrom. The base extends laterally away from the airfoil. The airfoil extends axially from an airfoil leading edge portion to an airfoil trailing edge portion. The base has a humped area forward the airfoil leading edge portion.
摘要翻译：示例性翼型组件包括具有从其径向突出的翼型件的基座。基座横向延伸离开翼型。翼型件从翼型件前缘部分轴向延伸到翼型件后缘部分。基座具有朝向翼面前缘部分的隆起区域。

9. 发明授权

US07686567B2 Airfoil embodying mixed loading conventions 有权
标题翻译：机翼体现混合装载规则
公开(公告)号：US07686567B2
公开(公告)日：2010-03-30
申请号：US11303672
申请日：2005-12-16
申请人： Eric A. Grover , Thomas J. Praisner
发明人： Eric A. Grover , Thomas J. Praisner
IPC分类号： F04D27/02
CPC分类号： F01D5/141 , F05D2250/71 , Y02T50/673 , Y10S416/02
摘要： A high-lift airfoil embodying a combination of loading conventions in a single design specifically to reduce and control total pressure losses that occur in the flow channels between airfoils employed in turbomachinery applications is disclosed herein. The mixed-loading high-lift airfoil designs embody and exhibit the best total profile and secondary loss characteristics possessed by both aft-loaded airfoil and front-loaded airfoil conventions through controlling the development and interaction of boundary layers forming along the surfaces of the airfoils and the endwalls in such applications. The mixed-loading high-lift airfoil may be utilized in both rotating and non-rotating turbomachinery applications.
摘要翻译：本文公开了一种实现单一设计中的装载约定的组合的高升力翼型，专门用于减少和控制在涡轮机械应用中使用的翼型之间的流动通道中发生的总压力损失。混合装载的高升力翼型设计通过控制沿着翼型件的表面形成的边界层的发展和相互作用，体现并展现了后装翼型和前装翼型惯例所具有的最佳总轮廓和二次损失特性，以及这些应用程序中的端壁。混合装载的高升力翼型件可用于旋转和非旋转涡轮机械应用中。

10. 发明授权

US07251592B1 Boundary layer transition model 有权
标题翻译：边界层过渡模型
公开(公告)号：US07251592B1
公开(公告)日：2007-07-31
申请号：US10921486
申请日：2004-08-18
申请人： Thomas J. Praisner , Eric A. Grover
发明人： Thomas J. Praisner , Eric A. Grover
IPC分类号： G06G7/48 , G06G7/50
CPC分类号： G06F17/5018 , G06F2217/16
摘要： A method for analyzing performance of an airfoil includes determining: an estimated laminar separation location; a freestream turbulence intensity; a momentum thickness; and a turbulence length scale. Based upon the freestream turbulence intensity, momentum thickness, and turbulence length scale, a first momentum thickness Reynolds number associated with a first estimated laminar/turbulent boundary transition location along the airfoil is determined. If the estimated laminar separation location is downstream of the first estimated transition, the first estimated transition is used to determine a spatial domain for running a turbulent flow model. If the estimated laminar separation location is upstream of the first estimated transition, a second estimated transition location is used to determine a spatial domain for running the turbulent flow model. The second estimated transition location is determined as a function of a momentum thickness Reynolds number associated with the estimated laminar separation location.
摘要翻译：用于分析翼型件的性能的方法包括确定：估计的层流分离位置; 自由流湍流强度; 动量厚度; 和湍流长度尺度。基于自由湍流强度，动量厚度和湍流长度尺度，确定与沿着翼型的第一估计层流/湍流边界转变位置相关联的第一动量厚度雷诺数。如果估计的层流分离位置在第一估计转变的下游，则使用第一估计转换来确定用于运行湍流模型的空间域。如果估计层流分离位置在第一估计转变的上游，则使用第二估计转换位置来确定用于运行湍流模型的空间域。第二估计转换位置被确定为与估计层流分离位置相关联的动量厚度雷诺数的函数。

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