Ling Fang Liu

US Patent:

20130340406, Dec 26, 2013

Filed:

Feb 10, 2012

Appl. No.:

13/370486

Inventors:

Edward J. Gallagher - West Hartford CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US

International Classification:

F02K 3/06

US Classification:

60204, 602261, 416223 A

Abstract:

A gas turbine engine includes a spool, a turbine coupled with the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool and a gear assembly coupled between the propulsor and the spool such that rotation of the spool results in rotation of the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge such that the chord forms a stagger angle α with the axis. The stagger angle α is less than 62 at all positions along the span, with said hub being at 0% of the span and the tip being at 100% of the span.

US Patent:

20190063227, Feb 28, 2019

Filed:

Jul 30, 2018

Appl. No.:

16/048981

Inventors:

- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US

International Classification:

F01D 5/14
F01D 5/02
F02C 3/04
F02C 3/14
F01D 15/12

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.

US Patent:

20180016912, Jan 18, 2018

Filed:

Sep 15, 2017

Appl. No.:

15/706025

Inventors:

- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US

International Classification:

F01D 5/14

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.

US Patent:

20170241268, Aug 24, 2017

Filed:

Aug 22, 2014

Appl. No.:

15/113607

Inventors:

- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US

International Classification:

F01D 5/14
F02C 7/36
F02C 3/04

Abstract:

An airfoil for a turbine engine includes 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 relationship between an axial leading edge location and a span position that is at least a third order polynomial with a generally U-shaped curve having an initial negative slope followed by a positive slope. The positive slope leans aftward and the negative slope leans forward. The curve has a critical point in the range of 30-50% span position at which the curve changes from the negative slope to the positive slope. The curve is generally linear from 55% span to 75% span and has a positive slope that increases at a rate of about 0.0875 inch (2.22 mm) per 1% span, +/−0.04 inch (1.01 mm) per 1% span.

US Patent:

20170191494, Jul 6, 2017

Filed:

Mar 27, 2017

Appl. No.:

15/470462

Inventors:

- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefiedl CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US

International Classification:

F04D 29/32
F04D 29/38
F02K 3/06
F04D 19/00

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 curve that corresponds 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. 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. A negative dihedral corresponds to pressure side-leaning. The trailing edge sweep angle is positive from 0%-95% span. A positive-most trailing edge sweep angle is within the range of 10 to 20 in the range of 40-70% span position. The airfoil is a fan blade for the turbine engine.

US Patent:

20170184119, Jun 29, 2017

Filed:

Mar 16, 2017

Appl. No.:

15/460333

Inventors:

- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US

International Classification:

F04D 29/38
F02K 3/06
F04D 29/32
F02C 3/04

Abstract:

A gas turbine engine includes a combustion section arranged between a compressor section and a turbine section that extend in an axial direction. A fan section is arranged upstream from the compressor section. An airfoil is arranged in one of the fan section, the compressor section and the turbine section. The airfoil includes 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 leading edge that is projected onto a plane from various views and the plane is perpendicular to a viewing direction which corresponds to the various views. The plane is parallel with the axial direction in a 0 view. The various views include the 0 view which projects into an axial plane in the axial direction. A 90 view projects into a tangential plane in a tangential direction normal to the axial direction and views between the 0 and 90 views. The airfoil has a maximum leading edge projection in a 20 to view. The radial direction is normal to the axial and tangential directions.

US Patent:

20170130586, May 11, 2017

Filed:

Jan 27, 2017

Appl. No.:

15/418115

Inventors:

- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US

International Classification:

F01D 5/14

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.

US Patent:

20170030197, Feb 2, 2017

Filed:

Oct 17, 2016

Appl. No.:

15/294939

Inventors:

- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US

International Classification:

F01D 5/14
F02K 3/06
F04D 29/38
F02C 3/107

Abstract:

An airfoil for a turbine engine includes 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 stacking offset and a span position that includes at least one positive and negative slope. The positive slope leans aftward and the negative slope leans forward relative to an engine axis. The positive slope crosses an initial axial stacking offset corresponding to the 0% span position at a zero-crossing position. A first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve. A second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve. A ratio of the second to first axial stacking offset X2/X1 is less than 2.0.