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公开(公告)号：US10415391B2
公开(公告)日：2019-09-17
申请号：US14702051
申请日：2015-05-01
摘要： The present disclosure relates generally a gas turbine engine and a rotor therefor. The rotor may include a symmetric rim thereon to prevent the propagation of induced vibratory responses. The rim may have one or more sloping surfaces to prevent the re-attachment of boundary layer flow.
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公开(公告)号：US09752587B2
公开(公告)日：2017-09-05
申请号：US14301893
申请日：2014-06-11
发明人： Benjamin E. Fishler
CPC分类号： F04D27/0215 , F01D9/045 , F01D17/143 , F02C6/08 , F04D27/023 , F04D29/4206 , F04D29/682
摘要： The present disclosure relates to shroud bleed in centrifugal compressors. An air-limiting component 130 may be located adjacent to a shroud 120. The shroud 120 may have a primary bleed slot 210, and the air-limiting component 130 may have a secondary bleed slot 310. The primary bleed slot 210 and the secondary bleed slot 310 may overlap at an effective bleed slot location. The air-limiting component 130 may rotate relative to the shroud 120, which may change a streamwise location of the effective bleed slot.
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公开(公告)号：US09976422B2
公开(公告)日：2018-05-22
申请号：US14768964
申请日：2013-12-31
发明人： Benjamin E. Fishler
IPC分类号： F01D5/14 , F01D5/04 , F04D29/24 , F04D29/30 , F04D29/66 , F04D29/22 , F04D29/28 , F04D29/68 , F01D5/02
CPC分类号： F01D5/146 , F01D5/02 , F01D5/048 , F04D29/2272 , F04D29/24 , F04D29/242 , F04D29/245 , F04D29/284 , F04D29/30 , F04D29/666 , F04D29/681 , F05D2220/32 , F05D2250/90
摘要： The presently disclosed embodiments utilize flow from a higher-energy portion of flow within the impeller flow path and inject it into the lower-energy portion of the flow path to re-energize the flow, delaying the onset of, or minimizing, large (and inefficient, entropy-generating) re-circulation zones in the flow field. By making a spanwise cut along the chord length of the splitter blade (variable blade clearance from leading edge to trailing edge), additional secondary flow occurs within the flow passages as the higher pressure flow on the pressure side of the blade can now spill over into the low-pressure suction side of the blade.
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公开(公告)号：US09963974B2
公开(公告)日：2018-05-08
申请号：US13658184
申请日：2012-10-23
发明人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Steven R. Falconer , Ralph E. Gordon , Jesus A. Garcia , Dan G. Sapiro , Ulrike Kaul , Gregory G. Johnson , Benjamin E. Fishler
CPC分类号： F01D5/16 , F01D5/005 , F01D5/141 , F01D9/04 , F05D2240/122 , F05D2260/81 , G01M13/00 , Y10T29/49318
摘要： A reduction in excitation amplitudes affecting turbine blade durability in a turbine nozzle assembly having a plurality of vanes and turbine blades, includes: identifying a turbine blade design of the turbine nozzle assembly; performing a modal model analysis of at least one of the turbine blades in the turbine blade design; reducing aerodynamic impact by ensuring that each of the turbine blades is free of aero-excitation from an upstream flow at the vanes in an operating speed range; identifying blade natural frequencies with respect to the nozzle vanes; and modifying a trailing edge of at least one of the vanes to reduce the excitation amplitudes.
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公开(公告)号：US20150330225A1
公开(公告)日：2015-11-19
申请号：US14702051
申请日：2015-05-01
摘要： The present disclosure relates generally a gas turbine engine and a rotor therefor. The rotor may include a symmetric rim thereon to prevent the propagation of induced vibratory responses. The rim may have one or more sloping surfaces to prevent the re-attachment of boundary layer flow.
摘要翻译： 本发明总体上涉及燃气涡轮发动机及其转子。 转子可以包括其上的对称边缘，以防止感应振动响应的传播。 边缘可以具有一个或多个倾斜表面以防止边界层流的再附着。
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公开(公告)号：US20160003050A1
公开(公告)日：2016-01-07
申请号：US14768964
申请日：2013-12-31
发明人： Benjamin E. Fishler
CPC分类号： F01D5/146 , F01D5/02 , F01D5/048 , F04D29/2272 , F04D29/24 , F04D29/242 , F04D29/245 , F04D29/284 , F04D29/30 , F04D29/666 , F04D29/681 , F05D2220/32 , F05D2250/90
摘要： The presently disclosed embodiments utilize flow from a higher-energy portion of flow within the impeller flow path and inject it into the lower-energy portion of the flow path to re-energize the flow, delaying the onset of, or minimizing, large (and inefficient, entropy-generating) re-circulation zones in the flow field. By making a spanwise cut along the chord length of the splitter blade (variable blade clearance from leading edge to trailing edge), additional secondary flow occurs within the flow passages as the higher pressure flow on the pressure side of the blade can now spill over into the low-pressure suction side of the blade.
摘要翻译： 目前公开的实施例利用来自叶轮流动路径内的较高能量部分的流动并将其注入流动路径的较低能量部分，以重新激励流动，延迟大的（和 低效，熵产生）流场中的再循环区域。 通过沿着分流叶片的翼弦长度（从前缘到后缘的可变叶片间隙）进行翼展横切，在流动通道内发生额外的二次流动，因为叶片的压力侧上的较高压力流现在可以溢出 叶片的低压吸力侧。
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公开(公告)号：US20140369804A1
公开(公告)日：2014-12-18
申请号：US14301893
申请日：2014-06-11
发明人： Benjamin E. Fishler
IPC分类号： F04D27/02
CPC分类号： F04D27/0215 , F01D9/045 , F01D17/143 , F02C6/08 , F04D27/023 , F04D29/4206 , F04D29/682
摘要： The present disclosure relates to shroud bleed in centrifugal compressors. An air-limiting component 130 may be located adjacent to a shroud 120. The shroud 120 may have a primary bleed slot 210, and the air-limiting component 130 may have a secondary bleed slot 310. The primary bleed slot 210 and the secondary bleed slot 310 may overlap at an effective bleed slot location. The air-limiting component 130 may rotate relative to the shroud 120, which may change a streamwise location of the effective bleed slot.
摘要翻译： 本公开涉及离心式压缩机中的护罩流出。 空气限制部件130可以邻近护罩120定位。护罩120可以具有主出口狭槽210，并且空气限制部件130可以具有辅助排放槽310.主排出狭槽210和次要排出口 槽310可以在有效的出血槽位置处重叠。 空气限制部件130可以相对于护罩120旋转，这可以改变有效排放槽的流动位置。
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公开(公告)号：US20140112760A1
公开(公告)日：2014-04-24
申请号：US13658184
申请日：2012-10-23
发明人： Loc Quang Duong , Xiaolan Hu , Gao Yang , Steven R. Falconer , Ralph E. Gordon , Jesus A. Garcia , Dan G. Sapiro , Ulrike Kaul , Gregory G. Johnson , Benjamin E. Fishler
CPC分类号： F01D5/16 , F01D5/005 , F01D5/141 , F01D9/04 , F05D2240/122 , F05D2260/81 , G01M13/00 , Y10T29/49318
摘要： A reduction in excitation amplitudes affecting turbine blade durability in a turbine nozzle assembly having a plurality of vanes and turbine blades, includes: identifying a turbine blade design of the turbine nozzle assembly; performing a modal model analysis of at least one of the turbine blades in the turbine blade design; reducing aerodynamic impact by ensuring that each of the turbine blades is free of aero-excitation from an upstream flow at the vanes in an operating speed range; identifying blade natural frequencies with respect to the nozzle vanes; and modifying a trailing edge of at least one of the vanes to reduce the excitation amplitudes.
摘要翻译： 在具有多个叶片和涡轮叶片的涡轮喷嘴组件中影响涡轮叶片耐久性的激励振幅的减小包括：识别涡轮喷嘴组件的涡轮叶片设计; 对涡轮叶片设计中的至少一个涡轮叶片执行模态模型分析; 通过确保每个涡轮机叶片在操作速度范围内不受来自叶片上游流动的空气激励而减小空气动力学冲击; 识别叶片相对于喷嘴叶片的固有频率; 以及修改至少一个叶片的后缘以减小激励振幅。
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