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公开(公告)号：US09869191B2
公开(公告)日：2018-01-16
申请号：US14433700
申请日：2013-04-17
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Glen E. Potter , Barry M. Ford
CPC classification number: F01D9/04 , F01D1/023 , F01D5/021 , F01D5/141 , F01D25/24 , F02C3/107 , F02K3/06 , F05D2220/32 , F05D2220/36 , F05D2230/60 , F05D2240/12 , Y10T29/49323
Abstract: A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15°.
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公开(公告)号：US09752439B2
公开(公告)日：2017-09-05
申请号：US14996351
申请日：2016-01-15
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
CPC classification number: F01D5/141 , F04D29/324 , F05D2220/32 , F05D2260/40311 , Y02T50/672 , Y02T50/673
Abstract: An airfoil arrangement of a turbine engine according to an example of the present disclosure includes adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope.
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公开(公告)号：US20170241268A1
公开(公告)日：2017-08-24
申请号：US15113607
申请日：2014-08-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
Abstract: An airfoil for a turbine engine includes pressure and suction sides extending 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 an axial leading edge location and a span position that is at least a third order polynomial with a generally U-shaped curve having an initial negative slope followed by a positive slope. The positive slope leans aftward and the negative slope leans forward. The curve has a critical point in the range of 30-50% span position at which the curve changes from the negative slope to the positive slope. The curve is generally linear from 55% span to 75% span and has a positive slope that increases at a rate of about 0.0875 inch (2.22 mm) per 1% span, +/−0.04 inch (1.01 mm) per 1% span.
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公开(公告)号：US20170184119A1
公开(公告)日：2017-06-29
申请号：US15460333
申请日：2017-03-16
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
Abstract: A gas turbine engine includes a combustion section arranged between a compressor section and a turbine section that extend in an axial direction. A fan section is arranged upstream from the compressor section. An airfoil is arranged in one of the fan section, the compressor section and the turbine section. The airfoil includes pressure and suction sides extending 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 leading edge that is projected onto a plane from various views and the plane is perpendicular to a viewing direction which corresponds to the various views. The plane is parallel with the axial direction in a 0° view. The various views include the 0° view which projects into an axial plane in the axial direction. A 90° view projects into a tangential plane in a tangential direction normal to the axial direction and views between the 0° and 90° views. The airfoil has a maximum leading edge projection in a 20° to 40° view. The radial direction is normal to the axial and tangential directions.
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公开(公告)号：US20170167503A1
公开(公告)日：2017-06-15
申请号：US15115779
申请日：2015-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
CPC classification number: F04D29/324 , F01D5/141 , F02C3/06 , F02C7/36 , F02K3/06 , F04D29/325 , F04D29/38 , F04D29/544 , F05D2220/3216 , F05D2220/323 , F05D2240/301 , F05D2240/35 , F05D2250/70 , F05D2250/71 , F05D2260/4031 , Y02T50/672 , Y02T50/673
Abstract: An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.
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Patent Agency Ranking
公开(公告)号：US20160348691A1
公开(公告)日：2016-12-01
申请号：US15114922
申请日：2015-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 35° from 0% span to at least 50% span.
Abstract translation: 涡轮发动机的翼型包括从0％跨度位置到100％跨度位置沿径向方向延伸的压力和吸力侧。 翼型在交错角度和跨度位置之间有一个关系，这个关系定义了一个交错角度的曲线，该角度大于从0％跨度到至少50％跨度的35°。
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公开(公告)号：US20160341211A1
公开(公告)日：2016-11-24
申请号：US15113870
申请日：2015-02-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear.
Abstract translation: 具有齿轮架构的涡轮发动机的压缩机翼片包括从0％跨度位置到100％跨度位置沿径向方向延伸的压力和吸力侧。 翼型在定义非线性曲线的切向堆积偏移和跨度位置之间具有关系。
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公开(公告)号：US20160201607A1
公开(公告)日：2016-07-14
申请号：US14695373
申请日：2015-04-24
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Shari L. Bugaj
CPC classification number: 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
Abstract: 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.
Abstract translation: 燃气涡轮发动机包括芯流路，旁通流路和布置在旁通流路和芯流路的入口的推进器。 推进器包括一排推进刀片。 该行包括不超过20个推进刀片。 推进器在推进刀片上的压力比介于约1.2和约1.7之间。
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公开(公告)号：US20160076380A1
公开(公告)日：2016-03-17
申请号：US14827059
申请日：2015-08-14
Applicant: United Technologies Corporation
Inventor： Daniel K. Van Ness , Mark A. Stephens , Edward J. Gallagher , Joseph C. Straccia , Vikram A. Kumar
CPC classification number: F01D5/141 , F01D5/142 , F01D9/041 , F02C3/04 , F04D29/324 , F04D29/544 , F05D2220/32 , F05D2220/323 , F05D2240/121 , F05D2240/122 , F05D2240/301 , F05D2240/303 , F05D2240/304 , F05D2240/35 , F05D2250/71 , Y02T50/672 , Y02T50/673
Abstract: A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge, an outer diameter edge, a trailing edge and a leading edge. The leading edge has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge. The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction.
Abstract translation: 描述燃气涡轮发动机部件。 燃气涡轮发动机部件包括内径边缘，外径边缘，后缘和前缘。 前缘在前缘的整个跨度的整个跨度上具有正（后）气动扫描。 燃气涡轮发动机部件在组件的基本上整个跨度上具有大于50度的外倾角。 燃气涡轮发动机部件可以具有径向方向上的部件的不对称切向堆叠。
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公开(公告)号：US20160069187A1
公开(公告)日：2016-03-10
申请号：US14626130
申请日：2015-02-19
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
CPC classification number: F01D5/141 , F04D29/324 , F05D2220/32 , F05D2260/40311 , Y02T50/672 , Y02T50/673
Abstract: An airfoil of a turbine engine according to an example of the present disclosure includes, among other things, pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope.
Abstract translation: 根据本公开的示例的涡轮发动机的翼型尤其包括在径向方向上从0％跨度位置延伸到100％跨度位置的压力和吸力侧。 翼型具有间隙/弦比和跨度位置之间的关系，其定义具有带有负斜率的部分的间隙/弦比的曲线。
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