Patents by Inventor William E. Alford

William E. Alford 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).

  • Publication number: 20190219337
    Abstract: A heat exchanger includes an additively manufactured manifold. The manifold includes an inlet feed manifold and an outlet feed manifold, and a plurality of hypotubes fluidly coupled to the manifold. The hypotubes are round in cross-section, wherein each of the hypotubes has a diameter that has a first value between 0.03 inches and 0.3 inches, and wherein each of the hypotubes has a wall thickness that has a second value between 0.001 inches and 0.0.015 inches.
    Type: Application
    Filed: January 18, 2018
    Publication date: July 18, 2019
    Inventors: Wendell V. Twelves, David U. Furrer, William E. Alford
  • Publication number: 20190033020
    Abstract: A thin-walled heat exchanger includes a component having at least one thermal transfer structure. The thermal transfer structure includes a wall having a thickness ranging from about 0.003 in to about 0.010 in.
    Type: Application
    Filed: July 27, 2017
    Publication date: January 31, 2019
    Inventors: Wendell V. Twelves, JR., William E. Alford
  • Patent number: 7856824
    Abstract: Cooling systems for an aircraft are provided. In an embodiment, a system includes an engine nacelle, an engine, a bypass duct, and a heat exchanger. The engine nacelle includes an airflow inlet. The engine is housed in the engine nacelle in flow communication with the airflow inlet. The bypass duct extends between the engine nacelle and the engine is in flow communication with the airflow inlet. The bypass duct includes an outer wall and an opening formed therein. The heat exchanger is integrated with the engine and is disposed over the opening of the bypass duct outer wall between the bypass duct outer wall and the engine nacelle.
    Type: Grant
    Filed: June 25, 2007
    Date of Patent: December 28, 2010
    Assignee: Honeywell International Inc.
    Inventors: Morris G. Anderson, William E. Alford, Michael L. Trego, Ron Haugland, David K. Winstanley
  • Patent number: 7594794
    Abstract: A variable geometry inlet guide vane assembly that reduces stress placed on downstream compressor blades in gas turbine engines. The invention circumferential leans upstream guide vanes, pushing engine core air flow radially. This allows for aerodynamic stresses on the downstream blades to be reduced. The invention overcomes the difference in movement between a unison ring and a vane arm by providing a hinge in conjunction with a spherical bearing that couples to the unison ring.
    Type: Grant
    Filed: August 24, 2006
    Date of Patent: September 29, 2009
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Om Parkash Sharma, Gabriel L. Suciu, William E. Alford
  • Publication number: 20080314047
    Abstract: Cooling systems for an aircraft are provided. In an embodiment, a system includes an engine nacelle, an engine, a bypass duct, and a heat exchanger. The engine nacelle includes an airflow inlet. The engine is housed in the engine nacelle in flow communication with the airflow inlet. The bypass duct extends between the engine nacelle and the engine is in flow communication with the airflow inlet. The bypass duct includes an outer wall and an opening formed therein. The heat exchanger is integrated with the engine and is disposed over the opening of the bypass duct outer wall between the bypass duct outer wall and the engine nacelle.
    Type: Application
    Filed: June 25, 2007
    Publication date: December 25, 2008
    Applicant: HONEYWELL INTERNATIONAL, INC.
    Inventors: Morris G. Anderson, William E. Alford, Michael L. Trego, Ron Haugland, David K. Winstanley
  • Publication number: 20080050220
    Abstract: A variable geometry inlet guide vane assembly that reduces stress placed on downstream compressor blades in gas turbine engines. The invention circumferential leans upstream guide vanes, pushing engine core air flow radially. This allows for aerodynamic stresses on the downstream blades to be reduced. The invention overcomes the difference in movement between a unison ring and a vane arm by providing a hinge in conjunction with a spherical bearing that couples to the unison ring.
    Type: Application
    Filed: August 24, 2006
    Publication date: February 28, 2008
    Inventors: Brian D. Merry, Om Parkash Sharma, Gabriel L. Suciu, William E. Alford