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公开(公告)号：US20220106965A1
公开(公告)日：2022-04-07
申请号：US17551349
申请日：2021-12-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
IPC: F04D29/38 , F01D5/14 , F01D17/16 , F01D25/24 , F02C3/04 , F02C7/36 , F04D29/32 , F04D29/54 , F02K3/06
Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side that extends in a radially outward direction from a 0% span position to a 100% span position. The airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis. The airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle at 100% span is greater than the stagger angle at 50% span.
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公开(公告)号：US20200149545A1
公开(公告)日：2020-05-14
申请号：US16741918
申请日：2020-01-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
IPC: F04D29/38 , F04D29/32 , F02K3/06 , F02C7/36 , F02C3/04 , F01D25/24 , F01D17/16 , F01D5/14 , F04D29/54
Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is provided in the compressor section outside the high pressure compressor section and 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 the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle has a positive slope from 20% span to 100% span.
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公开(公告)号：US20200096005A1
公开(公告)日：2020-03-26
申请号：US16681187
申请日：2019-11-12
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
Abstract: A gas turbine engine includes a combustor section, a compressor section, and a turbine section. A high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. A low pressure compressor is counter-rotating relative to the fan blades and downstream from the fan section. The airfoil outside of the compressor section is rotatable relative to an engine static structure. The airfoil includes pressure and suction sides extending from a 0% span position to a 100% span position. A relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span. The leading edge angle is defined by a tangential plane normal to an engine axis and a line tangent to a camber mean line at the leading edge.
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公开(公告)号：US10060263B2
公开(公告)日：2018-08-28
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.
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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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Patent Agency Ranking
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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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：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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