Patents by Inventor Timothy Charles Nash
Timothy Charles Nash 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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Patent number: 11473434Abstract: An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.Type: GrantFiled: October 16, 2019Date of Patent: October 18, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Timothy Charles Nash, Gary A. Zess, Eric A. Grover, Jin Hu
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Patent number: 11261737Abstract: A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.35-1.65 inches. A chord length at 50% span is 1.20-1.60 inches. At least two of: a first mode resonance frequency is 2858±10% Hz; a second mode resonance frequency is 4916±10% Hz; a third mode resonance frequency is 7160±10% Hz; a fourth mode resonance frequency is 10268±10% Hz; a fifth mode resonance frequency is 14235±10% Hz; and a sixth mode resonance frequency is 15088±10% Hz.Type: GrantFiled: January 15, 2018Date of Patent: March 1, 2022Assignee: Raytheon Technologies CorporationInventors: Daniel A. Snyder, Edwin Otero, Di Wu, Timothy Charles Nash, Brandon W. Spangler
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Publication number: 20210115803Abstract: An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.Type: ApplicationFiled: October 16, 2019Publication date: April 22, 2021Inventors: Timothy Charles Nash, Gary A. Zess, Eric A. Grover, Jin Hu
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Patent number: 10774650Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A curvature inflection point is located between 30% and 70% of an axial chord length of the airfoil.Type: GrantFiled: October 12, 2017Date of Patent: September 15, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Timothy Charles Nash, Thomas J. Praisner
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Patent number: 10563512Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of leading edge radius to maximum thickness is between 0.40 (r/Tmax) and 0.45 (r/Tmax) and a ratio of leading edge radius to axial chord length is between 0.17 (r/bx) and 0.27 (r/bx).Type: GrantFiled: October 25, 2017Date of Patent: February 18, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Timothy Charles Nash, Carey Clum
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Publication number: 20200024984Abstract: An airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.Type: ApplicationFiled: December 19, 2018Publication date: January 23, 2020Inventors: Andrew S. Aggarwala, Timothy Charles Nash, Eunice Allen-Bradley, Eric A. Grover
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Patent number: 10508550Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.Type: GrantFiled: October 25, 2017Date of Patent: December 17, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Timothy Charles Nash, Loubriel Ramirez
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Patent number: 10280756Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from a radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of maximum thickness to axial chord length is between 0.40 (Tmax/bx) and 0.65 (Tmax/bx).Type: GrantFiled: October 2, 2017Date of Patent: May 7, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Timothy Charles Nash, Wolfgang Balzer
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Publication number: 20190120059Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.Type: ApplicationFiled: October 25, 2017Publication date: April 25, 2019Inventors: Timothy Charles Nash, Loubriel Ramirez
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Publication number: 20190120058Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of leading edge radius to maximum thickness is between 0.40 (r/Tmax) and 0.45 (r/Tmax) and a ratio of leading edge radius to axial chord length is between 0.17 (r/bx) and 0.27 (r/bx).Type: ApplicationFiled: October 25, 2017Publication date: April 25, 2019Inventors: Timothy Charles Nash, Carey Clum
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Publication number: 20190112930Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A curvature inflection point is located between 30% and 70% of an axial chord length of the airfoil.Type: ApplicationFiled: October 12, 2017Publication date: April 18, 2019Inventors: Timothy Charles Nash, Thomas J. Praisner
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Publication number: 20190106989Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner portion of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A bowed tip portion extends perpendicular to a mid-camber line of the airfoil.Type: ApplicationFiled: October 9, 2017Publication date: April 11, 2019Inventor: Timothy Charles Nash
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Publication number: 20190101001Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from a radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of maximum thickness to axial chord length is between 0.40 (Tmax/bx) and 0.65 (Tmax/bx).Type: ApplicationFiled: October 2, 2017Publication date: April 4, 2019Inventors: Timothy Charles Nash, Wolfgang Balzer
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Patent number: 9938854Abstract: A gas turbine engine includes an array of airfoils. Each airfoil includes a first circumferentially extreme position. The first circumferentially extreme positions of the airfoils are circumferentially spaced apart from one another a pitch. Each airfoil includes a second circumferentially extreme position circumferentially spaced from the first circumferentially extreme position in an angular spacing that is at least one half the pitch.Type: GrantFiled: May 14, 2015Date of Patent: April 10, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Alex J. Simpson, Timothy Charles Nash
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Publication number: 20150361826Abstract: A gas turbine engine includes an array of airfoils. Each airfoil includes a first circumferentially extreme position. The first circumferentially extreme positions of the airfoils are circumferentially spaced apart from one another a pitch. Each airfoil includes a second circumferentially extreme position circumferentially spaced from the first circumferentially extreme position in an angular spacing that is at least one half the pitch.Type: ApplicationFiled: May 14, 2015Publication date: December 17, 2015Inventors: Alex J. Simpson, Timothy Charles Nash
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Patent number: 9115588Abstract: A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface that extends from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.Type: GrantFiled: July 2, 2012Date of Patent: August 25, 2015Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Timothy Charles Nash
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Patent number: 9004861Abstract: An example blade assembly includes, among other things a blade tip having a pressure side and a suction side, and a plurality of grooves within the blade tip. At least one of the grooves has a contour that is different than both a contour of the pressure side and a contour of the suction side.Type: GrantFiled: May 10, 2012Date of Patent: April 14, 2015Assignee: United Technologies CorporationInventors: Timothy Charles Nash, Andrew S. Aggarwala
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Publication number: 20140000281Abstract: A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface that extends from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.Type: ApplicationFiled: July 2, 2012Publication date: January 2, 2014Inventor: Timothy Charles Nash
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Patent number: 8602740Abstract: An airfoil comprises an external surface formed in substantial conformance with a plurality of cross sections. Each of the cross sections has an axial chord and an offset at a corresponding fractional span as set forth in Table 1. Each of the cross sections is described by a set of Cartesian coordinates defined at the corresponding fractional span as set forth in Table 3.Type: GrantFiled: September 8, 2010Date of Patent: December 10, 2013Assignee: United Technologies CorporationInventors: Jason L. O'Hearn, Timothy Charles Nash
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Publication number: 20130302162Abstract: An example blade assembly includes, among other things a blade tip having a pressure side and a suction side, and a plurality of grooves within the blade tip. At least one of the grooves has a contour that is different than both a contour of the pressure side and a contour of the suction side.Type: ApplicationFiled: May 10, 2012Publication date: November 14, 2013Inventors: Timothy Charles Nash, Andrew S. Aggarwala