Patents by Inventor Barry M. Ford
Barry M. Ford has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20170191494Abstract: 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.Type: ApplicationFiled: March 27, 2017Publication date: July 6, 2017Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Publication number: 20170184119Abstract: 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.Type: ApplicationFiled: March 16, 2017Publication date: June 29, 2017Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Publication number: 20170130586Abstract: 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.Type: ApplicationFiled: January 27, 2017Publication date: May 11, 2017Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Patent number: 9638201Abstract: An air bleed system for a jet engine is provided. The air bleed system is located in the low pressure compressor chamber and comprises a movable bleed valve and a stationary, annular bleed case having a forward section and an aft section and ligaments connecting the two sections and providing structural support to the bleed case. The ligaments are machined from the bleed case into an aerodynamic shape that maximizes the flow of air through the bleed ports.Type: GrantFiled: June 20, 2012Date of Patent: May 2, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Ryan Edward LeBlanc, Kevin J. Cummings, Barry M. Ford
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Patent number: 9605542Abstract: 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, and 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, and a negative dihedral corresponds to pressure side-leaning.Type: GrantFiled: February 18, 2015Date of Patent: March 28, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Patent number: 9599064Abstract: A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. 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 maximum chord length projection that is not in an axial view.Type: GrantFiled: February 19, 2015Date of Patent: March 21, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Patent number: 9574574Abstract: 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.Type: GrantFiled: June 24, 2016Date of Patent: February 21, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Publication number: 20170030197Abstract: 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.Type: ApplicationFiled: October 17, 2016Publication date: February 2, 2017Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Publication number: 20170023004Abstract: In one exemplary embodiment, 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 geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve. The airfoil extends from a root. A zero tangential reference point corresponds to tangential center of the root. YLE corresponds to a tangential distance from a leading edge to the reference point at a given span position. YTE corresponds to a tangential distance from a trailing edge to the reference point at a given span position. Yd corresponds to a tangential stacking offset at a given span position. (YLE?Yd)/(Yd?YTE) at 40% span position is about 1.5 and (YLE?Yd)/(Yd?YTE) at 20% span position is about 2.Type: ApplicationFiled: August 25, 2014Publication date: January 26, 2017Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Publication number: 20170023005Abstract: 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 tangential leading edge location and a span position that corresponds to a curve that is at least a third order polynomial with a generally S-shaped curve that has an initial negative slope followed by a positive slope and then a second negative slope. The positive slope leans toward the suction side and the negative slopes lean toward the pressure side.Type: ApplicationFiled: August 25, 2014Publication date: January 26, 2017Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Publication number: 20160341071Abstract: The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.Type: ApplicationFiled: December 15, 2014Publication date: November 24, 2016Applicant: United Technologies CorporationInventors: Andrew G. Alarcon, Royce E. Tatton, Barry M. Ford, Linda S. Li, Matthew A. Turner
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Publication number: 20160341212Abstract: 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 geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve. The airfoil extends from a root and a zero axial reference point corresponds to axial center of the root. XLE corresponds to an axial distance from a leading edge to the reference point at a given span position. XTE corresponds to a axial distance from a trailing edge to the reference point at a given span position. Xd corresponds to an axial stacking offset at a given span position. (XLE?Xd)/(Xd?XTE) at 100% span position is about 1 and (XLE?Xd)/(Xd?XTE) at 90% span position is about 1.Type: ApplicationFiled: August 22, 2014Publication date: November 24, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Patent number: 9482097Abstract: 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 is at least a third order polynomial curve 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.Type: GrantFiled: August 27, 2015Date of Patent: November 1, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Publication number: 20160298643Abstract: 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.Type: ApplicationFiled: June 24, 2016Publication date: October 13, 2016Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Publication number: 20160238023Abstract: 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 total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm). The curve is at least a third order polynomial and has an initial positive slope.Type: ApplicationFiled: March 8, 2016Publication date: August 18, 2016Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Patent number: 9399917Abstract: 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 is a fan blade for a gas turbine engine. 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.Type: GrantFiled: October 7, 2015Date of Patent: July 26, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Patent number: 9353628Abstract: 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 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.Type: GrantFiled: February 17, 2015Date of Patent: May 31, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Patent number: 9347323Abstract: 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 total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains generally constant or has a decreasing total chord length from the first peak to the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm).Type: GrantFiled: February 17, 2015Date of Patent: May 24, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Publication number: 20160032728Abstract: An airfoil of 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 tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starts at the 0% span position is either zero or positive. The first critical point is less than 15% span.Type: ApplicationFiled: August 26, 2015Publication date: February 4, 2016Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
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Publication number: 20160024929Abstract: 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 is a fan blade for a gas turbine engine. 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.Type: ApplicationFiled: October 7, 2015Publication date: January 28, 2016Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford