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1. 发明授权

US08702398B2 High camber compressor rotor blade 有权
标题翻译：高外倾压缩机转子叶片
公开(公告)号：US08702398B2
公开(公告)日：2014-04-22
申请号：US13072027
申请日：2011-03-25
申请人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
发明人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , Y02T50/673
摘要： A rotor blade having an airfoil for a compressor is described. The airfoil has an airfoil root, an airfoil tip located at a spanwise distance from the airfoil root, a leading edge extending from the airfoil root to the airfoil tip, an inner span region (“S1”) between the airfoil root and a first height location on the airfoil leading edge, a midspan region (“S2”) between the first height location and a second height location on the airfoil leading edge located radially outward from the first height location; an outer span region (“S3”) between the second height location and the airfoil tip, wherein the airfoil has a normalized camber profile such that the normalized camber increases in the outer span region in a spanwise direction towards the tip and is more than 2.2 in the outer span region.
摘要翻译：描述了具有用于压缩机的翼型的转子叶片。所述翼型件具有翼型根部，所述翼型端部位于与所述翼型根的翼展距离处，从所述翼型根延伸到所述翼型端部的前缘，所述翼型根部与所述翼型根部之间的内部跨度区域（“S1”）在翼型前缘上的位置，位于第一高度位置与位于第一高度位置径向向外的翼型件前缘上的第二高度位置之间的中跨区域（“S2”）; 在第二高度位置和翼型尖端之间的外跨距区域（“S3”），其中翼型件具有归一化的弧形轮廓，使得归一化的外倾角在翼跨方向上朝向顶端的外跨距区域增加，并且大于2.2 在外跨区域。

2. 发明授权

US08684698B2 Compressor airfoil with tip dihedral 有权
标题翻译：压缩机翼型具有尖端二面体
公开(公告)号：US08684698B2
公开(公告)日：2014-04-01
申请号：US13071996
申请日：2011-03-25
申请人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
发明人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
IPC分类号： F01D5/12
CPC分类号： F04D29/324 , F01D5/141 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2250/71 , Y02T50/673
摘要： An airfoil for a compressor is described. The airfoil has a root, an airfoil tip, a leading edge, a trailing edge, airfoil pressure and suction sides extending between the leading edge and the trailing edge. The airfoil has an inner span region and an outer span region and the trailing edge has a dihedral profile such that the trailing edge dihedral angle decreases in at least a portion of the inner span region and the outer span region.
摘要翻译：描述了用于压缩机的翼型件。翼型件具有根部，翼型端头，前缘，后缘，在前缘和后缘之间延伸的翼型压力和吸力侧。翼型件具有内跨区域和外跨距区域，并且后缘具有双面轮廓，使得后缘二面角在内跨距区域和外跨距区域的至少一部分中减小。

3. 发明申请

US20120244005A1 HIGH CAMBER COMPRESSOR ROTOR BLADE 有权
标题翻译：高档压缩机转子叶片
公开(公告)号：US20120244005A1
公开(公告)日：2012-09-27
申请号：US13072027
申请日：2011-03-25
申请人： Andrew BREEZE-STRINGFELLOW , David Scott Clark , Brent F. Beacher
发明人： Andrew BREEZE-STRINGFELLOW , David Scott Clark , Brent F. Beacher
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , Y02T50/673
摘要： A rotor blade having an airfoil for a compressor is described. The airfoil has an airfoil root, an airfoil tip located at a spanwise distance from the airfoil root, a leading edge extending from the airfoil root to the airfoil tip, an inner span region (“S1”) between the airfoil root and a first height location on the airfoil leading edge, a midspan region (“S2”) between the first height location and a second height location on the airfoil leading edge located radially outward from the first height location; an outer span region (“S3”) between the second height location and the airfoil tip, wherein the airfoil has a normalized camber profile such that the normalized camber increases in the outer span region in a spanwise direction towards the tip and is more than 2.2 in the outer span region.
摘要翻译：描述了具有用于压缩机的翼型的转子叶片。所述翼型件具有翼型根部，所述翼型端部位于与所述翼型根的翼展距离处，从所述翼型根延伸到所述翼型端部的前缘，所述翼型根部与所述翼型根部之间的第一高度在翼型前缘上的位置，位于第一高度位置与位于第一高度位置径向向外的翼型件前缘上的第二高度位置之间的中跨区域（“S2”）; 在第二高度位置和翼型尖端之间的外跨距区域（“S3”），其中翼型件具有归一化的弧形轮廓，使得归一化的外倾角在翼跨方向上朝向顶端的外跨距区域增加，并且大于2.2 在外跨区域。

4. 发明授权

US09074483B2 High camber stator vane 有权
标题翻译：高弧度定子叶片
公开(公告)号：US09074483B2
公开(公告)日：2015-07-07
申请号：US13072091
申请日：2011-03-25
申请人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
发明人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
IPC分类号： F01D9/00 , F01D5/14 , F04D29/54
CPC分类号： F01D5/148 , F01D5/141 , F04D29/544 , F05D2240/121 , F05D2240/303 , F05D2250/71 , Y02T50/671 , Y02T50/673
摘要： A stator vane for a compressor is described. The stator vane has an airfoil root, an airfoil tip, a leading edge, a trailing edge, an inner span region, a midspan region and an outer span region, wherein the stator vane has a normalized camber profile that increases in the outer span region in a spanwise direction towards the tip and is more than 1.4 in the outer span region.
摘要翻译：描述了用于压缩机的定子叶片。定子叶片具有翼型根部，翼型端头，前缘，后缘，内跨距，中跨区域和外跨距区域，其中定子叶片具有在外跨距区域中增加的归一化的弧形轮廓在朝向尖端的翼展方向上，并且在外跨度区域中大于1.4。

5. 发明申请

US20120243975A1 COMPRESSOR AIRFOIL WITH TIP DIHEDRAL 有权
标题翻译：压缩机空气与提示DIHEDRAL
公开(公告)号：US20120243975A1
公开(公告)日：2012-09-27
申请号：US13071996
申请日：2011-03-25
申请人： Andrew BREEZE-STRINGFELLOW , David Scott Clark , Brent F. Beacher
发明人： Andrew BREEZE-STRINGFELLOW , David Scott Clark , Brent F. Beacher
IPC分类号： F01D11/08 , F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2250/71 , Y02T50/673
摘要： An airfoil for a compressor is described. The airfoil has a root, an airfoil tip, a leading edge, a trailing edge, airfoil pressure and suction sides extending between the leading edge and the trailing edge. The airfoil has an inner span region and an outer span region and the trailing edge has a dihedral profile such that the trailing edge dihedral angle decreases in at least a portion of the inner span region and the outer span region.
摘要翻译：描述了用于压缩机的翼型件。翼型件具有根部，翼型端头，前缘，后缘，在前缘和后缘之间延伸的翼型压力和吸力侧。翼型件具有内跨区域和外跨距区域，并且后缘具有双面轮廓，使得后缘二面角在内跨距区域和外跨距区域的至少一部分中减小。

6. 发明授权

US06331100B1 Doubled bowed compressor airfoil 有权
标题翻译：双压缩压缩机翼型
公开(公告)号：US06331100B1
公开(公告)日：2001-12-18
申请号：US09455826
申请日：1999-12-06
申请人： Hsin-Tuan Liu , Robert B. Dickman , Kenneth W. Krabacher , Gregory T. Steinmetz , Brent F. Beacher , Bryan K. Doloresco
发明人： Hsin-Tuan Liu , Robert B. Dickman , Kenneth W. Krabacher , Gregory T. Steinmetz , Brent F. Beacher , Bryan K. Doloresco
IPC分类号： F01D514
CPC分类号： F04D29/324 , F01D5/141 , F05D2250/70 , Y02T50/671 , Y02T50/673
摘要： A compressor airfoil includes pressure and suction sides extending from root to tip and between leading and trailing edges. Transverse sections have respective chords and camber lines. Centers of gravity of the sections are aligned along a double bowed stacking axis for improving performance.
摘要翻译：压缩机翼片包括从根部到顶端以及在前缘和后缘之间延伸的压力和吸力侧。横截面具有各自的和弦和曲线。这些部分的重心沿双弓形堆叠轴线对齐，以提高性能。

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