公开(公告)号：US10794192B2

公开(公告)日：2020-10-06

申请号：US16048981

申请日：2018-07-30

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

IPC: F01D5/14 ,  F01D5/02 ,  F01D15/12 ,  F02C3/14 ,  F02C3/04

Abstract: An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 0° to 10° in a range of 10-20% span position. The trailing edge sweep angle is in a range of the trailing edge sweep angle is positive from 0% span to at least 95% span.

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：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：US10288009B2

公开(公告)日：2019-05-14

申请号：US15252689

申请日：2016-08-31

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon

IPC: F01D5/14 ,  F02K3/06 ,  F01D17/14 ,  F02K1/06

Abstract: A gas turbine engine includes a bypass flow passage that has an inlet and defines a bypass ratio in a range of approximately 8.5 to 13.5. A fan is arranged at the inlet. A first turbine is coupled with a first shaft such that rotation of the first turbine will drive the fan. A first compressor is coupled with the first shaft and includes three stages, and a second turbine is coupled with a second shaft and includes two stages. The fan includes a row of 16 (N) fan blades that has a solidity value (R) that is from 1.0 to 1.2 and a ratio of N/R that is from 13.3 to 16.0.

公开(公告)号：US20190063227A1

公开(公告)日：2019-02-28

申请号：US16048981

申请日：2018-07-30

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

IPC: F01D5/14 ,  F01D5/02 ,  F02C3/04 ,  F02C3/14 ,  F01D15/12

Abstract: An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 0° to 10° in a range of 10-20% span position. The trailing edge sweep angle is in a range of the trailing edge sweep angle is positive from 0% span to at least 95% span.

公开(公告)号：US10036257B2

公开(公告)日：2018-07-31

申请号：US14624666

申请日：2015-02-18

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

IPC: F01D5/14 ,  F01D5/02 ,  F01D15/12 ,  F02C3/14 ,  F02C3/04

CPC classification number: F01D5/141 ,  F01D5/02 ,  F01D15/12 ,  F02C3/04 ,  F02C3/14 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2250/71 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.