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公开(公告)号：US20120251325A1
公开(公告)日：2012-10-04
申请号：US13433314
申请日：2012-03-29
CPC分类号： F01D5/143 , F01D5/3038 , F01D11/008 , Y10T29/49316
摘要： A rotor for a turbomachine includes at least one moving blade row including a plurality of moving blades disposed adjacent to one another in a circumferential direction with respect to an axis of rotation. Each one of the plurality of moving blades includes a blade leaf and a blade root having an outer face, the outer face of the blade root including a blade root curved end wall contour adjacent the blade leaf in the circumferential direction. The blade root curved end wall contour has a concave curvature in an axial sectional plane of the rotor. At least one rotor shaft includes a reception slot for a respective one of the at least one moving blade row extending in the circumferential direction. Each of the plurality of moving blades is inserted into the reception slot via a respective blade root.
摘要翻译： 用于涡轮机的转子包括至少一个活动叶片排，其包括相对于旋转轴线在圆周方向上彼此相邻设置的多个活动叶片。 多个移动叶片中的每一个包括具有外表面的叶片叶片和叶片根部，叶片根部的外表面包括在圆周方向上与叶片叶片相邻的叶根弯曲端壁轮廓。 叶片根弯曲端壁轮廓在转子的轴向截面中具有凹曲率。 至少一个转子轴包括用于沿圆周方向延伸的至少一个活动叶片列中的相应一个的接收槽。 多个移动叶片中的每一个经由相应的叶根插入到接收槽中。
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公开(公告)号：US08915716B2
公开(公告)日：2014-12-23
申请号：US13433314
申请日：2012-03-29
CPC分类号： F01D5/143 , F01D5/3038 , F01D11/008 , Y10T29/49316
摘要： A rotor for a turbomachine includes at least one moving blade row including a plurality of moving blades disposed adjacent to one another in a circumferential direction with respect to an axis of rotation. Each one of the plurality of moving blades includes a blade leaf and a blade root having an outer face, the outer face of the blade root including a blade root curved end wall contour adjacent the blade leaf in the circumferential direction. The blade root curved end wall contour has a concave curvature in an axial sectional plane of the rotor. At least one rotor shaft includes a reception slot for a respective one of the at least one moving blade row extending in the circumferential direction. Each of the plurality of moving blades is inserted into the reception slot via a respective blade root.
摘要翻译： 用于涡轮机的转子包括至少一个活动叶片排，其包括相对于旋转轴线在圆周方向上彼此相邻设置的多个活动叶片。 多个移动叶片中的每一个包括具有外表面的叶片叶片和叶片根部，叶片根部的外表面包括在圆周方向上与叶片叶片相邻的叶根弯曲端壁轮廓。 叶片根弯曲端壁轮廓在转子的轴向截面中具有凹曲率。 至少一个转子轴包括用于沿圆周方向延伸的至少一个活动叶片列中的相应一个的接收槽。 多个移动叶片中的每一个经由相应的叶根插入到接收槽中。
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公开(公告)号：US20100260610A1
公开(公告)日：2010-10-14
申请号：US12756729
申请日：2010-04-08
IPC分类号： F01D5/14
CPC分类号： F04D29/32 , F01D5/141 , F01D5/20 , F05D2250/74
摘要： The disclosure provides blades, and the modification thereof, for stages 18-22 of an axial compressor wherein the blades have reduced susceptibility to tip cracking. The blades and blades manufactured by the provided method have a thickened profile that results in reduced stress in response to multi frequency impulses and can have increased frequency response of the chord wise bending mode.
摘要翻译： 本公开为轴向压缩机的级18-22提供叶片及其修改，其中叶片具有降低的尖端开裂敏感性。 通过所提供的方法制造的叶片和叶片具有加厚的轮廓，其导致响应于多频率脉冲而减小的应力，并且可以增加弦弯曲模式的频率响应。
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公开(公告)号：US08449261B2
公开(公告)日：2013-05-28
申请号：US12756729
申请日：2010-04-08
IPC分类号： B64C27/46
CPC分类号： F04D29/32 , F01D5/141 , F01D5/20 , F05D2250/74
摘要： The disclosure provides blades, and the modification thereof, for stages 18-22 of an axial compressor wherein the blades have reduced susceptibility to tip cracking. The blades and blades manufactured by the provided method have a thickened profile that results in reduced stress in response to multi frequency impulses and can have increased frequency response of the chord wise bending mode.
摘要翻译： 本公开为轴向压缩机的级18-22提供叶片及其修改，其中叶片具有降低的尖端开裂敏感性。 通过所提供的方法制造的叶片和叶片具有加厚的轮廓，其导致响应于多频率脉冲而减小的应力，并且可以增加弦弯曲模式的频率响应。
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公开(公告)号：US09291059B2
公开(公告)日：2016-03-22
申请号：US12646561
申请日：2009-12-23
CPC分类号： F01D5/141 , F04D29/324 , F05D2240/301 , F05D2250/70
摘要： The present disclosure provides an improved first stage airfoil for a compressor blade having a unique chord length (CD), stagger angle (γ) and camber angle (Δβ). The stagger angle (γ) and camber angle (Δβ) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.
摘要翻译： 本公开提供了一种用于压缩机叶片的改进的第一级翼型件，其具有独特的弦长（CD），交错角（γ）和外倾角（＆Dgr; bgr）。 交错角（γ）和外倾角（＆Dgr;＆bgr）提供改进的空气动力学，而弦长（CD）提供降低的翼型重量。
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公开(公告)号：US09004853B2
公开(公告)日：2015-04-14
申请号：US13556788
申请日：2012-07-24
申请人： Luis Puerta , Marco Micheli , Wolfgang Kappis , Gabriel Dunkel
发明人： Luis Puerta , Marco Micheli , Wolfgang Kappis , Gabriel Dunkel
CPC分类号： F02C7/1435 , F02C3/305 , F02C9/18 , F04D27/0215 , F04D27/0238 , F04D29/522 , F04D29/5846 , F04D29/705 , F05D2260/212 , Y10T29/49826
摘要： An axial compressor is disclosed for compressing air, such as for a gas turbine. The axial compressor can include a rotor, having a multiplicity of rotor blades, and rotor casing. The casing and rotor can form an annular gas passage. Outside the gas passage an annular and concentric bleed air chamber, can include at least one bleed air slot in functional communication with the gas passage. At least one injection device having at least one nozzle which can inject the fluid into the gas passage via the bleed air slot.
摘要翻译： 公开了用于压缩空气的轴向压缩机，例如用于燃气轮机。 轴向压缩机可以包括具有多个转子叶片的转子和转子壳体。 壳体和转子可以形成环形气体通道。 在气体通道外部，环形和同心的排气室可以包括与气体通道功能性连通的至少一个排气口。 至少一个注射装置具有至少一个能够经由排气槽将流体注入气体通道的喷嘴。
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公开(公告)号：US20110150660A1
公开(公告)日：2011-06-23
申请号：US12646561
申请日：2009-12-23
IPC分类号： F04D29/38
CPC分类号： F01D5/141 , F04D29/324 , F05D2240/301 , F05D2250/70
摘要： The present disclosure provides an improved first stage airfoil for a compressor blade having a unique chord length (CD), stagger angle (γ) and camber angle (Δβ). The stagger angle (γ) and camber angle (Δβ) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.
摘要翻译： 本公开提供了一种用于压缩机叶片的改进的第一级翼型件，其具有独特的弦长（CD），交错角（γ）和外倾角（＆Dgr; bgr）。 交错角（γ）和外倾角（＆Dgr;＆bgr）提供改进的空气动力学，而弦长（CD）提供降低的翼型重量。
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公开(公告)号：US20130058760A1
公开(公告)日：2013-03-07
申请号：US13556788
申请日：2012-07-24
申请人： Luis PUERTA , Marco Micheli , Wolfgang Kappis , Gabriel Dunkel
发明人： Luis PUERTA , Marco Micheli , Wolfgang Kappis , Gabriel Dunkel
CPC分类号： F02C7/1435 , F02C3/305 , F02C9/18 , F04D27/0215 , F04D27/0238 , F04D29/522 , F04D29/5846 , F04D29/705 , F05D2260/212 , Y10T29/49826
摘要： An axial compressor is disclosed for compressing air, such as for a gas turbine. The axial compressor can include a rotor, having a multiplicity of rotor blades, and rotor casing. The casing and rotor can form an annular gas passage. Outside the gas passage an annular and concentric bleed air chamber, can include at least one bleed air slot in functional communication with the gas passage. At least one injection device having at least one nozzle which can inject the fluid into the gas passage via the bleed air slot.
摘要翻译： 公开了用于压缩空气的轴向压缩机，例如用于燃气轮机。 轴向压缩机可以包括具有多个转子叶片的转子和转子壳体。 壳体和转子可以形成环形气体通道。 在气体通道外部，环形和同心的排气室可以包括与气体通道功能性连通的至少一个排气口。 至少一个注射装置具有至少一个能够经由排气槽将流体注入气体通道的喷嘴。
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公开(公告)号：US09297259B2
公开(公告)日：2016-03-29
申请号：US13523260
申请日：2012-06-14
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/301 , F05D2250/74
摘要： A compressor component having an improved airfoil profile so as to eliminate previously known vibratory issues in the blade tip is disclosed. By altering the airfoil profile throughout its span, the natural frequency of the airfoil is altered so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1.
摘要翻译： 公开了具有改进的翼型轮廓以便消除先前已知的叶片尖端的振动问题的压缩机部件。 通过在其整个跨度中改变翼面轮廓，翼型件的固有频率被改变，使得与压缩机的关键发动机顺序不一致。 此外，本发明提供了根据表1的坐标的新的翼型轮廓。
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公开(公告)号：US20130336799A1
公开(公告)日：2013-12-19
申请号：US13523260
申请日：2012-06-14
CPC分类号： F01D5/141 , F05D2240/301 , F05D2250/74
摘要： A compressor component having an improved airfoil profile so as to eliminate previously known vibratory issues in the blade tip is disclosed. By altering the airfoil profile throughout its span, the natural frequency of the airfoil is altered so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1.
摘要翻译： 公开了具有改进的翼型轮廓以便消除先前已知的叶片尖端的振动问题的压缩机部件。 通过在其整个跨度中改变翼面轮廓，翼型件的固有频率被改变，使得与压缩机的关键发动机顺序不一致。 此外，本发明提供了根据表1的坐标的新的翼型轮廓。
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