公开(公告)号：US20150198045A1

公开(公告)日：2015-07-16

申请号：US14669784

申请日：2015-03-26

Applicant: United Technologies Corporation

Inventor： Joseph C. Straccia

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D5/20 ,  F05D2200/22 ,  F05D2240/125 ,  F05D2240/305 ,  F05D2240/307 ,  F05D2250/71 ,  Y10S416/02 ,  Y10S416/05

Abstract: A turbomachine blade with a localized dihedral feature has a high order polynomial shaped curve region.

Abstract translation: 具有局部二面特征的涡轮机叶片具有高阶多项式形状曲线区域。

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.

公开(公告)号：US10760447B1

公开(公告)日：2020-09-01

申请号：US15869312

申请日：2018-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D9/02 ,  F01D25/04 ,  F02C3/06 ,  F04D29/54 ,  F04D29/66 ,  F02K3/06

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 3.84-4.14 inch (97.5-105.1 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 1.16-1.46 inch (29.5-37.1 mm). The airfoil element includes at least two of a first mode with a frequency of 326±10% Hz, a second mode with a frequency of 1252±10% Hz, a third mode with a frequency of 2475±10% Hz, a fourth mode with a frequency of 2951±10% Hz, a fifth mode with a frequency of 4356±10% Hz and a sixth mode with a frequency of 6086±10% Hz.

公开(公告)号：US20200149546A1

公开(公告)日：2020-05-14

申请号：US16591046

申请日：2019-10-02

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 ,  F04D29/54 ,  F01D5/14 ,  F04D29/32 ,  F02C3/067

Abstract: A compressor 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 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. A positive sweep angle is in the rearward direction. The airfoil has a relationship between trailing edge sweep angle and span position defined by a curve in which the trailing edge sweep angle is negative at 0% span and changes less than 10° from 0% span to 90% span.

公开(公告)号：US10605259B2

公开(公告)日：2020-03-31

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 ,  F01D5/14 ,  F02C3/04 ,  F02C7/36 ,  F04D19/02

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：US10590775B2

公开(公告)日：2020-03-17

申请号：US15115501

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: F01D5/14 ,  F01D9/04

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 stagger angle and span position that defines a curve with a stagger angle that is greater than 32° from 90% span to 100% span.

公开(公告)号：US10584715B2

公开(公告)日：2020-03-10

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

IPC: F04D29/38 ,  F04D29/54 ,  F01D25/24 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/32

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.

公开(公告)号：US10570915B2

公开(公告)日：2020-02-25

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 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/38

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.

公开(公告)号：US09726021B2

公开(公告)日：2017-08-08

申请号：US14669784

申请日：2015-03-26

Applicant: United Technologies Corporation

Inventor： Joseph C. Straccia

IPC: F01D5/14 ,  F01D5/20

CPC classification number: F01D5/141 ,  F01D5/20 ,  F05D2200/22 ,  F05D2240/125 ,  F05D2240/305 ,  F05D2240/307 ,  F05D2250/71 ,  Y10S416/02 ,  Y10S416/05

Abstract: A turbomachine blade with a localized dihedral feature has a high order polynomial shaped curve region.

公开(公告)号：US20170175760A1

公开(公告)日：2017-06-22

申请号：US15116287

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

CPC classification number: F04D29/324 ,  F01D5/141 ,  F01D17/162 ,  F02C3/04 ,  F02C7/36 ,  F04D19/02 ,  F04D29/325 ,  F04D29/544 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/121 ,  F05D2240/303 ,  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 extending in radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge dihedral angle and span position defined by a curve with the leading edge dihedral angle including 10° or less change from 0% span to 60% span.