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1. 发明授权

US10519971B2 Gas turbine engine airfoil 有权
公开(公告)号：US10519971B2
公开(公告)日：2019-12-31
申请号：US15113868
申请日：2014-08-22
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC分类号： F04D29/38 , F01D5/14 , F04D29/32 , F02C3/04 , F02C7/36 , F02K3/06
摘要： An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve. The airfoil extends from a root and a zero axial reference point corresponds to axial center of the root. XLE corresponds to an axial distance from a leading edge to the reference point at a given span position. XTE corresponds to a axial distance from a trailing edge to the reference point at a given span position. Xd corresponds to an axial stacking offset at a given span position. (XLE−Xd)/(Xd−XTE) at 100% span position is about 1 and (XLE−Xd)/(Xd−XTE) at 90% span position is about 1.

2. 发明申请

US20180328372A1 EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 审中-公开
公开(公告)号：US20180328372A1
公开(公告)日：2018-11-15
申请号：US15709567
申请日：2017-09-20
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon , Shari L. Bugaj
IPC分类号： F04D29/02 , F02K3/06 , F04D29/56 , F02C3/06
CPC分类号： F04D29/023 , F01D5/147 , F01D5/282 , F01D15/12 , F02C3/06 , F02C7/36 , F02K1/06 , F02K3/06 , F04D29/053 , F04D29/325 , F04D29/388 , F04D29/526 , F04D29/563 , F05D2220/32 , F05D2220/323 , F05D2220/327 , F05D2220/36 , F05D2260/4031 , F05D2300/603 , Y02T50/672
摘要： A gas turbine engine includes a gear assembly and a bypass flow passage that has an inlet. A fan is arranged within the bypass flow passage. A first turbine is coupled with a first shaft, which is coupled with the fan. A second turbine is coupled with a second shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes 12 to 14 (N) of the fan blades, a solidity value (R) at tips of the fan blades that is greater than 0.85 and less than 1.1, and a ratio of N/R that is from 9 to 20.

3. 发明申请

US20180230943A1 EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 审中-公开
公开(公告)号：US20180230943A1
公开(公告)日：2018-08-16
申请号：US15936552
申请日：2018-03-27
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon
IPC分类号： F02K3/06 , F02K1/06 , F01D17/14
CPC分类号： F02K3/06 , F01D17/14 , F02K1/06 , F05D2220/327 , F05D2260/4031
摘要： A gas turbine engine includes a bypass flow passage and a core flow passage. The bypass flow passage defines a bypass ratio in a range of approximately 8.5 to 13.5. A fan is located upstream of the bypass flow passage. The bypass flow passage includes an inlet and an outlet that define a design fan pressure ratio of approximately 1.3 to 1.55. A first, inner shaft and a second, outer shaft are concentric. A first turbine is coupled with the first shaft, and the first shaft is coupled with the fan. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number of the fan blades, the number (N) being 18, a solidity value (R) at tips of the fan blades that is from 1.0 to 1.1, and a ratio of N/R that is from 16.4 to 18.0.

4. 发明授权

US09988908B2 Gas turbine engine airfoil 有权
公开(公告)号：US09988908B2
公开(公告)日：2018-06-05
申请号：US15706025
申请日：2017-09-15
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/14 , F01D5/145 , F04D29/324 , F04D29/325 , F04D29/384 , F05D2220/32 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/38 , F05D2250/70 , Y02T50/672 , Y02T50/673
摘要： A gas turbine engine include a combustor section arranged between a compressor section and a turbine section. A fan section has multiple fan blades. A geared architecture couples the fan section to the turbine section or compressor section. The fan blades include an airfoil that has pressure and suction sides. The airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.

5. 发明授权

US09909505B2 Efficient, low pressure ratio propulsor for gas turbine engines 有权
公开(公告)号：US09909505B2
公开(公告)日：2018-03-06
申请号：US14695373
申请日：2015-04-24
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon , Shari L. Bugaj
IPC分类号： F02C7/36 , F02K1/06 , F02K3/06 , F01D5/28 , F01D5/14 , F01D15/12 , F04D29/02 , F04D29/053 , F04D29/32 , F04D29/38 , F04D29/52 , F04D29/56
CPC分类号： F02C7/36 , F01D5/147 , F01D5/282 , F01D15/12 , F02K1/06 , F02K3/06 , F04D29/023 , F04D29/053 , F04D29/325 , F04D29/388 , F04D29/526 , F04D29/563 , F05D2220/32 , F05D2220/327 , F05D2220/36 , F05D2260/4031 , F05D2300/603 , Y02T50/672
摘要： A gas turbine engine includes a core flow passage, a bypass flow passage, and a propulsor arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor includes a row of propulsor blades. The row includes no more than 20 of the propulsor blades. The propulsor has a pressure ratio between about 1.2 and about 1.7 across the propulsor blades.

6. 发明申请

US20180023511A1 EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 有权
公开(公告)号：US20180023511A1
公开(公告)日：2018-01-25
申请号：US15709540
申请日：2017-09-20
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon
IPC分类号： F02K3/06 , F02K1/06 , F01D17/14
CPC分类号： F02K3/06 , F01D17/14 , F02K1/06 , F05D2220/327 , F05D2260/4031
摘要： A gas turbine engine includes a bypass flow passage that has an inlet and defines a bypass ratio in a range of approximately 8.5 to 13.5. A fan is arranged within the bypass flow passage. A first turbine is a 5-stage turbine and is coupled with a first shaft, which is coupled with the fan. A first compressor is coupled with the first shaft and is a 3-stage compressor. A second turbine is coupled with a second shaft and is a 2-stage turbine. The fan includes a row of fan blades that extend from a hub. The row includes a number (N) of the fan blades, a solidity value (R) at tips of the fab blades, and a ratio of N/R that is from 14 to 16.

7. 发明授权

US09574574B2 Gas turbine engine airfoil 有权
标题翻译：燃气涡轮发动机翼型
公开(公告)号：US09574574B2
公开(公告)日：2017-02-21
申请号：US15191860
申请日：2016-06-24
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC分类号： F01D5/14 , F04D29/38 , F04D29/32
CPC分类号： F01D5/141 , F01D5/14 , F01D5/145 , F04D29/324 , F04D29/325 , F04D29/384 , F05D2220/32 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/38 , F05D2250/70 , Y02T50/672 , Y02T50/673
摘要： An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.
摘要翻译：用于涡轮发动机的翼型件包括具有压力和吸力侧的翼型件，所述翼型件在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型顶端处的100％跨度位置。翼型件具有前缘二面体和跨度位置之间的关系。前缘二面体从0％跨度位置到100％跨度位置为负。正二面对应于吸力侧倾，负二面对应于压力侧倾。翼型件具有后缘二面体和跨度位置之间的关系。后缘二面体从0％跨度位置到100％跨度位置为正。正二面对应于吸力侧倾，负二面对应于压力侧倾。

8. 发明申请

US20160377027A1 EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 审中-公开
标题翻译：高效的，用于气体涡轮发动机的低压比推进器
公开(公告)号：US20160377027A1
公开(公告)日：2016-12-29
申请号：US15252811
申请日：2016-08-31
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon
IPC分类号： F02K3/06 , F02K1/06
CPC分类号： F02K3/06 , F01D17/14 , F02K1/06 , F05D2220/327 , F05D2260/4031
摘要： A gas turbine engine includes a gear assembly, a bypass flow passage, and a core flow passage. The bypass flow passage includes an inlet. A fan is arranged at the inlet of the bypass flow passage. A first shaft and a second shaft are mounted for rotation about an engine central longitudinal axis. A first turbine is coupled with the first shaft such that rotation of the first turbine is configured to drive the fan, through the first shaft and gear assembly, at a lower speed than the first shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes 12 (N) of the fan blades, a solidity value (R) that is from 1.0 to 1.2, and a ratio of N/R that is from 10.0 to 12.0.
摘要翻译：燃气涡轮发动机包括齿轮组件，旁通流动通道和芯流动通道。旁通流路包括入口。在旁通流路的入口设有风扇。第一轴和第二轴安装成围绕发动机中心纵向轴线旋转。第一涡轮机与第一轴联接，使得第一涡轮的旋转被配置成以比第一轴低的速度通过第一轴和齿轮组件驱动风扇。风扇包括从轮毂延伸的轮毂和一排风扇叶片。该行包括12（N）个风扇叶片，固体值（R）为1.0至1.2，N / R比为10.0至12.0。

9. 发明申请

US20160341212A1 GAS TURBINE ENGINE AIRFOIL 审中-公开
标题翻译：气体涡轮发动机气翼
公开(公告)号：US20160341212A1
公开(公告)日：2016-11-24
申请号：US15113868
申请日：2014-08-22
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC分类号： F04D29/38 , F02K3/06 , F04D29/32 , F02C3/04 , F02C7/36
摘要： An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve. The airfoil extends from a root and a zero axial reference point corresponds to axial center of the root. XLE corresponds to an axial distance from a leading edge to the reference point at a given span position. XTE corresponds to a axial distance from a trailing edge to the reference point at a given span position. Xd corresponds to an axial stacking offset at a given span position. (XLE−Xd)/(Xd−XTE) at 100% span position is about 1 and (XLE−Xd)/(Xd−XTE) at 90% span position is about 1.
摘要翻译：用于涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。翼型几何对应于轴向前缘和后缘曲线以及轴向堆叠偏移曲线。翼型从根部延伸，零轴向参考点对应于根部的轴向中心。 XLE对应于在给定跨度位置处从前缘到参考点的轴向距离。 XTE对应于在给定跨度位置处从后缘到参考点的轴向距离。 Xd对应于给定跨度位置处的轴向堆积偏移。（XLE-Xd）/（Xd-XTE）在100％跨度位置约为1，（XLE-Xd）/（Xd-XTE）在90％跨度位置约为1。

10. 发明申请

US20160238023A1 GAS TURBINE ENGINE AIRFOIL 审中-公开
标题翻译：气体涡轮发动机气翼
公开(公告)号：US20160238023A1
公开(公告)日：2016-08-18
申请号：US15063594
申请日：2016-03-08
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC分类号： F04D29/38 , F02K3/04 , F02C3/14 , F02C7/36 , F04D29/32 , F02C3/04
CPC分类号： F04D29/384 , F01D5/141 , F02C3/04 , F02C3/14 , F02C7/36 , F02K3/04 , F04D29/325 , F05D2220/36 , F05D2240/35 , F05D2250/71 , F05D2250/713 , F05D2250/75 , F05D2260/4031 , F05D2270/3013 , Y02T50/672 , Y02T50/673
摘要： An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm). The curve is at least a third order polynomial and has an initial positive slope.
摘要翻译：用于涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。翼型具有总弦长和跨度位置之间的关系，并且对应于从0％跨度位置到第一峰具有增加的总弦长的曲线。第一个峰出现在45-65％跨度位置的范围内，曲线或者保持恒定，或者从第一个峰到100％的跨度位置具有减小的总弦长。总和弦长度在8.2-10.5英寸（20.8-26.7厘米）范围内的0％跨度位置。该曲线是至少三阶多项式并具有初始正斜率。

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