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公开(公告)号：US20200173463A1
公开(公告)日：2020-06-04
申请号：US16667321
申请日：2019-10-29
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 that has a geared architecture 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 trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.
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公开(公告)号：US20170175758A1
公开(公告)日：2017-06-22
申请号：US15115714
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 , F02C3/04 , F02C7/36 , F04D19/02 , F04D29/325 , F04D29/544 , F05D2220/32 , F05D2220/3217 , F05D2240/121 , F05D2240/303 , F05D2240/35 , 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 leading edge angle and span position that defines a curve with a leading edge angle of less than 40° at 100% span.
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公开(公告)号：US20170167267A1
公开(公告)日：2017-06-15
申请号：US15115765
申请日：2015-02-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
IPC: F01D5/14
CPC classification number: F01D5/148 , F01D5/12 , F01D5/14 , F01D5/141 , F01D5/147 , F01D9/041 , Y02T50/672 , Y02T50/673
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 an axial leading edge position and span position that defines a curve with a negative slope from 90% span to 100% span. The negative slope corresponds to a forward leaning leading edge.
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公开(公告)号：US20160363128A1
公开(公告)日：2016-12-15
申请号：US15114167
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: F04D29/384 , F01D5/141 , F01D9/041 , F02C3/04 , F04D29/324 , F04D29/325 , F04D29/544 , F04D29/563 , F05D2220/32 , F05D2240/121 , F05D2240/303 , F05D2240/35 , Y02T50/672 , Y02T50/673
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 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.
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。 翼型件具有前缘角度和跨度位置之间的关系，其限定了具有从80％跨度到100％跨度的递减负斜率或正斜率中的至少一个的曲线。
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公开(公告)号：US20160356285A1
公开(公告)日：2016-12-08
申请号：US15113916
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 camber angle and span position that defines a curve with a decreasing camber angle from 80% span to 100% span.
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。 机翼具有外倾角和跨度位置之间的关系，其定义了从80％跨度到100％跨度的减小的外倾角的曲线。
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Patent Agency Ranking
公开(公告)号：US20160341213A1
公开(公告)日：2016-11-24
申请号：US15114745
申请日：2015-02-17
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: F04D29/384 , F01D5/141 , F02C3/067 , F04D29/324 , F04D29/544 , F04D29/563 , F05D2220/32 , F05D2220/3217 , F05D2240/121 , F05D2240/303 , Y02T50/672 , Y02T50/673
Abstract: A compressor airfoil of a turbine engine having a geared architecture includes 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 leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span. A negative sweep angle is in the forward direction, and a positive sweep angle is in the rearward direction.
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％跨度位置沿径向延伸的压力和吸力侧。 翼型具有前缘扫掠角度和跨度位置之间的关系，其中前缘扫掠角度在0％跨度处为正的曲线，并在小于80％跨距的跨度位置处跨过负前缘扫掠角度。 负扫描角在向前方向，正扫掠角处于向后方向。
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公开(公告)号：US20200149544A1
公开(公告)日：2020-05-14
申请号：US16740817
申请日：2020-01-13
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 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 arranged in the low pressure compressor 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 camber angle and span position that defines a curve with a decreasing camber angle within the range of 80% span to 100% span. The camber angle is less than 20° within the entire range of 40% span to 100% span.
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公开(公告)号：US10557477B2
公开(公告)日：2020-02-11
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.
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公开(公告)号：US10544802B2
公开(公告)日：2020-01-28
申请号：US15084643
申请日：2016-03-30
Applicant: United Technologies Corporation
Inventor： Lisa I. Brilliant , Becky E. Rose , Yuan Dong , Stanley J. Balamucki
Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.
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公开(公告)号：US20170175759A1
公开(公告)日：2017-06-22
申请号：US15116000
申请日：2015-02-17
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 extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential trailing edge position and span position that defines a curve with a non-positive slope from 90% span to 100% span. The non-positive slope corresponds to a pressure side-leaning trailing edge.
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