公开(公告)号：US20170159670A1

公开(公告)日：2017-06-08

申请号：US15115360

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

CPC classification number: F04D29/324 ,  F01D5/14 ,  F01D5/141 ,  F01D9/02 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/384 ,  F04D29/544 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2250/71 ,  F05D2260/4031 ,  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 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.

公开(公告)号：US09567858B2

公开(公告)日：2017-02-14

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

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：US10808544B1

公开(公告)日：2020-10-20

申请号：US15868181

申请日：2018-01-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Xuedong Zhou ,  Evan K. Fink ,  Joseph C. Straccia ,  Joseph Wieser ,  Konstantinos Panagiotis Giannakopoulos

IPC: F01D5/14 ,  F01D5/16 ,  F01D5/00 ,  F01D5/34 ,  F01D9/04 ,  F02C3/06

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 4.35-4.65 inch (110.5-118.1 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 2.45-2.75 inch (62.2-69.9 mm). The airfoil element includes at least two of a first mode with a frequency of 255±10% Hz, a second mode with a frequency of 818±10% Hz, a third mode with a frequency of 1439±10% Hz, a fourth mode with a frequency of 2035±10% Hz, a fifth mode with a frequency of 3033±10% Hz and a sixth mode with a frequency of 3740±10% Hz.

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。