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

IPC: F01D5/14 ,  F02C3/04 ,  F04D29/54 ,  F01D9/04 ,  F04D29/32

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。

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

IPC: F01D5/14 ,  F02C7/36 ,  F02C3/107 ,  F01D5/02 ,  F01D15/12

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。

公开(公告)号：US10788049B1

公开(公告)日：2020-09-29

申请号：US15871347

申请日：2018-01-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William R. Edwards ,  Stephen W. Milks ,  Steven J. Feigleson ,  Mark A. Stephens ,  Joseph C. Straccia

IPC: F02K3/06 ,  F04D29/54 ,  F04D29/02 ,  F04D29/66

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.59-2.89 inch (65.7-73.3 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.46-1.76 inch (37.1-44.7 mm). The airfoil element includes at least two of a first mode with a frequency of 703±10% Hz, a second mode with a frequency of 3574±10% Hz, a third mode with a frequency of 8100±10% Hz, a fourth mode with a frequency of 9450±10% Hz, a fifth mode with a frequency of 11116±10% Hz and a sixth mode with a frequency of 11620±10% Hz.

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

IPC: F04D29/54 ,  F02C7/36 ,  F04D29/32 ,  F02K3/072 ,  F01D5/14

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.

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

IPC: F04D29/32 ,  F04D29/54 ,  F04D19/02 ,  F02C7/36 ,  F02C3/04

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.

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.

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

IPC: F04D29/38 ,  F04D29/56 ,  F02K3/12 ,  F01D5/14 ,  F01D9/04 ,  F02C3/04 ,  F04D29/32 ,  F04D29/54

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。

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

IPC: F04D29/32 ,  F02K3/06 ,  F04D29/38 ,  F02C3/04 ,  F02C7/36

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。

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

IPC: F04D29/38 ,  F02C3/067 ,  F04D29/32

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。

公开(公告)号：US20200291955A1

公开(公告)日：2020-09-17

申请号：US16744749

申请日：2020-01-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Lisa I. Brilliant ,  Joseph C. Straccia ,  Stanley J. Balamucki ,  Mark A. Stephens ,  Kate Hudon

IPC: F04D29/32 ,  F04D29/54 ,  F01D5/14 ,  F01D9/02 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/38

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 an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.