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1.发明申请公开(公告)号：US20160208626A1
公开(公告)日：2016-07-21
申请号：US14599662
申请日：2015-01-19
发明人： Evan K. Fink , Joseph Steele
CPC分类号： F01D5/3023 , F01D5/141 , F01D5/143 , F01D5/145 , F01D5/34 , F02C3/04 , F05D2240/24 , F05D2240/30 , Y02T50/673
摘要： An integrally bladed rotor comprises a hub centered about an axis and having a plurality of blades extending radially outwardly of the axis across a span. Each of the blades includes an airfoil extending between a leading edge and a trailing edge, and having a pressure side and a suction side. The airfoil has a thicker portion at the trailing edge, and at a radially inner portion of the span, and over a limited percentage of the span, such that the thicker portion does not extend beyond 50 percent of the span. An axial distance is defined between the trailing edge and the leading edge. The thicker portion extends for less than 50 percent of the axial distance, and is on the pressure side. A gas turbine engine is also disclosed.
摘要翻译： 整体叶片转子包括以轴为中心的轮毂，并且具有跨过跨度径向向外延伸轴线的多个叶片。 每个叶片包括在前缘和后缘之间延伸并且具有压力侧和吸力侧的翼型件。 翼型件在后缘处具有较厚的部分，并且在跨度的径向内部部分和跨度的有限百分比之间，使得较厚部分不延伸超过跨度的50％。 在后缘和前缘之间限定轴向距离。 较厚的部分延伸小于轴向距离的50％，并且在压力侧。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US20160177756A1
公开(公告)日：2016-06-23
申请号：US14862361
申请日：2015-09-23
CPC分类号： F01D5/143 , F01D5/34 , F05D2250/232
摘要： The present disclosure includes airfoils for use in gas turbine engines. The airfoils comprise a fillet having a height of greater than 20% of the airfoil body span length. The airfoil may be a blade or a vane. Further, such airfoils may be used in the high pressure compressor section, as well as other gas turbine engine sections.
摘要翻译： 本公开包括用于燃气涡轮发动机的翼型件。 机翼包括高度大于翼型体跨距长度的20％的圆角。 翼型件可以是叶片或叶片。 此外，这样的翼型件可以用在高压压缩机部分以及其它燃气涡轮发动机部分中。
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公开(公告)号：US10267158B2
公开(公告)日：2019-04-23
申请号：US14862361
申请日：2015-09-23
摘要： The present disclosure includes airfoils for use in gas turbine engines. The airfoils comprise a fillet having a height of greater than 20% of the airfoil body span length. The airfoil may be a blade or a vane. Further, such airfoils may be used in the high pressure compressor section, as well as other gas turbine engine sections.
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公开(公告)号：US11231050B1
公开(公告)日：2022-01-25
申请号：US15869402
申请日：2018-01-12
摘要： A turbomachine airfoil element includes an airfoil having pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.60-0.70 inch (15.3-17.8 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.90-1.00 inch (22.9-25.5 mm). The airfoil element includes at least two of a first mode with a frequency of 5327±10% Hz, a second mode with a frequency of 8393±10% Hz, a third mode with a frequency of 16289±10% Hz, a fourth mode with a frequency of 25049±10% Hz and a fifth mode with a frequency of 27423±10% Hz.
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公开(公告)号：US10801336B1
公开(公告)日：2020-10-13
申请号：US15869290
申请日：2018-01-12
发明人： Charles P. Gendrich , Christopher St. Mary , Xuedong Zhou , Joseph Wieser , Zhen Wu , John Joseph Papalia , Kaliya Balamurugan , Joseph Steele , Jeff M. Carrico , Danoris Garcia-Chabrier
摘要： An airfoil has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.70-0.83 inch (17.8-21.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.34-0.45 inch (8.5-11.5 mm). The airfoil element includes at least three of a first mode with a frequency of 3748±15% Hz, a second mode with a frequency of 6416±15% Hz, a third mode with a frequency of 14418±15% Hz, a fourth mode with a frequency of 17417±15% Hz, a fifth mode with a frequency of 19326±15% Hz and a sixth mode with a frequency of 26648±15% Hz.
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