Patents by Inventor Charles A. Nash

Charles A. 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).

  • Patent number: 11261737
    Abstract: 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: Grant
    Filed: January 15, 2018
    Date of Patent: March 1, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Daniel A. Snyder, Edwin Otero, Di Wu, Timothy Charles Nash, Brandon W. Spangler
  • Publication number: 20210115803
    Abstract: 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: Application
    Filed: October 16, 2019
    Publication date: April 22, 2021
    Inventors: Timothy Charles Nash, Gary A. Zess, Eric A. Grover, Jin Hu
  • Patent number: 10774650
    Abstract: 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: Grant
    Filed: October 12, 2017
    Date of Patent: September 15, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Timothy Charles Nash, Thomas J. Praisner
  • Patent number: 10563512
    Abstract: 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: Grant
    Filed: October 25, 2017
    Date of Patent: February 18, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Timothy Charles Nash, Carey Clum
  • Publication number: 20200024984
    Abstract: 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: Application
    Filed: December 19, 2018
    Publication date: January 23, 2020
    Inventors: Andrew S. Aggarwala, Timothy Charles Nash, Eunice Allen-Bradley, Eric A. Grover
  • Patent number: 10508550
    Abstract: 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: Grant
    Filed: October 25, 2017
    Date of Patent: December 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Timothy Charles Nash, Loubriel Ramirez
  • Patent number: 10280756
    Abstract: 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: Grant
    Filed: October 2, 2017
    Date of Patent: May 7, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Timothy Charles Nash, Wolfgang Balzer
  • Publication number: 20190120058
    Abstract: 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: Application
    Filed: October 25, 2017
    Publication date: April 25, 2019
    Inventors: Timothy Charles Nash, Carey Clum
  • Publication number: 20190120059
    Abstract: 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: Application
    Filed: October 25, 2017
    Publication date: April 25, 2019
    Inventors: Timothy Charles Nash, Loubriel Ramirez
  • Publication number: 20190112930
    Abstract: 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: Application
    Filed: October 12, 2017
    Publication date: April 18, 2019
    Inventors: Timothy Charles Nash, Thomas J. Praisner
  • Publication number: 20190106989
    Abstract: 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: Application
    Filed: October 9, 2017
    Publication date: April 11, 2019
    Inventor: Timothy Charles Nash
  • Publication number: 20190101001
    Abstract: 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: Application
    Filed: October 2, 2017
    Publication date: April 4, 2019
    Inventors: Timothy Charles Nash, Wolfgang Balzer
  • Publication number: 20190085864
    Abstract: A flue exhaust fan has a configurable upwardly facing outlet for delivery of a mixture of gas and ambient air from the water heater or a furnace into either a vertical flue or a horizontal flue. Because the horizontal flue necessarily includes a 90° transition between the upwardly facing outlet and the horizontal flue, the horizontal flue has a greater flow resistance than the vertical flue. By installing a straight connector with a flow resistance element, the gas flow resistance encountered by the flue exhaust fan is the same for a vertical flue and a horizontal flue therefore requiring a single flue exhaust fan with a flow rating for installation with a horizontal flue or a vertical flue.
    Type: Application
    Filed: September 12, 2018
    Publication date: March 21, 2019
    Inventor: Charles Nash Simons
  • Patent number: 9938854
    Abstract: 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: Grant
    Filed: May 14, 2015
    Date of Patent: April 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Alex J. Simpson, Timothy Charles Nash
  • Patent number: 9388478
    Abstract: Disclosed are methods for recovering technetium from a highly alkaline solution. The highly alkaline solution can be a liquid waste solution from a nuclear waste processing system. Methods can include combining the solution with a reductant capable of reducing technetium at the high pH of the solution and adding to or forming in the solution an adsorbent capable of adsorbing the precipitated technetium at the high pH of the solution.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: July 12, 2016
    Assignee: Savannah River Nuclear Solutions, LLC
    Inventor: Charles A. Nash
  • Publication number: 20160177421
    Abstract: Disclosed are methods for recovering technetium from a highly alkaline solution. The highly alkaline solution can be a liquid waste solution from a nuclear waste processing system. Methods can include combining the solution with a reductant capable of reducing technetium at the high pH of the solution and adding to or forming in the solution an adsorbent capable of adsorbing the precipitated technetium at the high pH of the solution.
    Type: Application
    Filed: December 19, 2014
    Publication date: June 23, 2016
    Inventor: Charles A. Nash
  • Publication number: 20150361826
    Abstract: 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: Application
    Filed: May 14, 2015
    Publication date: December 17, 2015
    Inventors: Alex J. Simpson, Timothy Charles Nash
  • Patent number: 9115588
    Abstract: 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: Grant
    Filed: July 2, 2012
    Date of Patent: August 25, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Timothy Charles Nash
  • Patent number: 9004861
    Abstract: 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: Grant
    Filed: May 10, 2012
    Date of Patent: April 14, 2015
    Assignee: United Technologies Corporation
    Inventors: Timothy Charles Nash, Andrew S. Aggarwala
  • Publication number: 20140244350
    Abstract: A system for guiding business users through a process of globalizing their business and developing the plans and action items required to export specific products to specific markets. Other aspects and advantages of the present invention will become apparent from the following detailed description, taken in conjunction with the accompanying drawings, illustrating by way of example the principles of the present invention.
    Type: Application
    Filed: February 26, 2014
    Publication date: August 28, 2014
    Applicant: GLOBAL RESOURCE ASSOCIATES, INC.
    Inventors: William Gary Winget, Sandra Lou Renner, John Charles Nash