公开(公告)号：US10738627B2

公开(公告)日：2020-08-11

申请号：US15871248

申请日：2018-01-15

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Glen E. Potter ,  Barry M. Ford

IPC: F01D9/04 ,  F01D1/02 ,  F01D5/02 ,  F01D25/24 ,  F02K3/06 ,  F02C3/107 ,  F01D5/14

Abstract: A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15°.

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

IPC: F04D29/32 ,  F04D29/38 ,  F02K3/06 ,  F02C7/36 ,  F02C3/04 ,  F02K3/072 ,  F01D17/16 ,  F01D5/14

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.

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

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

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.

公开(公告)号：US10358924B2

公开(公告)日：2019-07-23

申请号：US15045343

申请日：2016-02-17

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Sue-Li Chuang

IPC: F04D29/38 ,  F02C3/10 ,  F04D29/32 ,  F01D5/14

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge and 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, facing pressure and suction sides of adjacent airfoils defining a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent airfoils. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side, the width converging and diverging along the channel for at least some span positions.

公开(公告)号：US10012150B2

公开(公告)日：2018-07-03

申请号：US15233142

申请日：2016-08-10

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Shari L. Bugaj

IPC: F02C7/36 ,  F02K1/06 ,  F02K3/06 ,  F01D5/28 ,  F01D5/14 ,  F01D15/12 ,  F04D29/02 ,  F04D29/053 ,  F04D29/32 ,  F04D29/38 ,  F04D29/52 ,  F04D29/56

CPC classification number: F04D29/023 ,  F01D5/147 ,  F01D5/282 ,  F01D15/12 ,  F02C3/06 ,  F02C7/36 ,  F02K1/06 ,  F02K3/06 ,  F04D29/053 ,  F04D29/325 ,  F04D29/388 ,  F04D29/526 ,  F04D29/563 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/327 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2300/603 ,  Y02T50/672

Abstract: A gas turbine engine includes a gear assembly and a bypass flow passage that includes an inlet and an outlet that define a design pressure ratio between 1.3 and 1.55. 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, through the first shaft and the gear assembly, at a lower speed than the first shaft. The fan includes a row of fan blades. The row includes 12-16 (N) fan blades, a solidity value (R) that is from 1.0 to 1.3, and a ratio of N/R that is from 10.0 to 16.

公开(公告)号：US20180016912A1

公开(公告)日：2018-01-18

申请号：US15706025

申请日：2017-09-15

Applicant: United Technologies Corporation

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

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D5/14 ,  F01D5/145 ,  F04D29/324 ,  F04D29/325 ,  F04D29/384 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/38 ,  F05D2250/70 ,  Y02T50/672 ,  Y02T50/673

Abstract: A gas turbine engine include a combustor section arranged between a compressor section and a turbine section. A fan section has multiple fan blades. A geared architecture couples the fan section to the turbine section or compressor section. The fan blades include an airfoil that has pressure and suction sides. The airfoil extends 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 relationship between a trailing edge dihedral and a span position. The trailing edge dihedral positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.

公开(公告)号：US20170191449A1

公开(公告)日：2017-07-06

申请号：US15252689

申请日：2016-08-31

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon

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

CPC classification number: F02K3/06 ,  F01D17/14 ,  F02K1/06 ,  F05D2220/327 ,  F05D2260/4031

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：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

IPC: F04D29/32 ,  F04D29/52 ,  F04D19/02 ,  F02K3/06 ,  F02C3/04 ,  F02C7/36

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.

公开(公告)号：US20170130586A1

公开(公告)日：2017-05-11

申请号：US15418115

申请日：2017-01-27

Applicant: United Technologies Corporation

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

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D5/14 ,  F01D5/145 ,  F04D29/324 ,  F04D29/325 ,  F04D29/384 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/38 ,  F05D2250/70 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend 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 relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning. The airfoil includes at least one of a least negative dihedral in a range of 5-15% span position, a least negative dihedral in a range of 0-10% span position and a least positive trailing edge dihedral in a 40%-55% span position.

公开(公告)号：US20170122336A1

公开(公告)日：2017-05-04

申请号：US15126371

申请日：2015-03-30

Applicant: United Technologies Corporation

Inventor： Scott C. Billings ,  Michael K. Gottschalk ,  William D. Owen ,  Edward J. Gallagher ,  Darryl Whitlow ,  Sue-Li Chuang ,  Mani Sadeghi

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

CPC classification number: F04D29/384 ,  F01D5/141 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/35 ,  F05D2250/70 ,  Y02T50/672 ,  Y02T50/673

Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends 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 that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.