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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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公开(公告)号：US08596986B2
公开(公告)日：2013-12-03
申请号：US13032912
申请日：2011-02-23
CPC分类号： F01D5/141 , F04D29/324 , F05D2250/74 , F05D2260/94 , Y02T50/671 , Y02T50/673
摘要： A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.
摘要翻译： 公开了具有根据表1的轮廓的翼型的压缩机部件。 压缩机部件，例如压缩机叶片，在翼型跨度的一部分上具有增加的厚度，以增加刚度。 此外，已经重新安装翼型件以在叶片根部/附接区域中引起压缩应力。 增加的刚度和复位翼型结合起来以改善压缩机部件的高循环疲劳能力。
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公开(公告)号：US20120213631A1
公开(公告)日：2012-08-23
申请号：US13032912
申请日：2011-02-23
CPC分类号： F01D5/141 , F04D29/324 , F05D2250/74 , F05D2260/94 , Y02T50/671 , Y02T50/673
摘要： A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.
摘要翻译： 公开了具有根据表1的轮廓的翼型的压缩机部件。 压缩机部件，例如压缩机叶片，在翼型跨度的一部分上具有增加的厚度，以增加刚度。 此外，已经重新安装翼型件以在叶片根部/附接区域中引起压缩应力。 增加的刚度和复位翼型结合起来以改善压缩机部件的高循环疲劳能力。
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公开(公告)号：US09523284B2
公开(公告)日：2016-12-20
申请号：US14087946
申请日：2013-11-22
申请人： Edward Len Miller , Stephen Wayne Fiebiger , Wes Carl Smith , Reiner Jochen Digele , Wilm Philipp Hecker , Andreas Martin Mattheiss
发明人： Edward Len Miller , Stephen Wayne Fiebiger , Wes Carl Smith , Reiner Jochen Digele , Wilm Philipp Hecker , Andreas Martin Mattheiss
摘要： A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor vane, has a decreased surface area over a portion of the airfoil chord length. The decreased surface area compressor vane operates in conjunction with a compressor blade having an increased surface area.
摘要翻译： 公开了具有根据表1的轮廓的翼型的压缩机部件。 压缩机部件，例如压缩机叶片，在翼型弦长度的一部分上具有减小的表面积。 减小的表面积压缩机叶片与具有增加的表面积的压缩机叶片一起操作。
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