Patents by Inventor Daniel K. Van Ness, II

Daniel K. Van Ness, II 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).

  • Gas turbine engines with heated cases
    Patent number: 10837313
    Abstract: A case for a gas turbine engine includes a case body defining an axially extending core flow path, a radially extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A lubricant conduit is connected to the case body and is in thermal communication with the structure-supporting member.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: November 17, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Steven Clarkson, Daniel K. Van Ness, II, Paul Thomas Rembish
  • Core case heating for gas turbine engines
    Patent number: 9896964
    Abstract: A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: February 20, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Steven Clarkson, Daniel K. Van Ness, II, Paul Thomas Rembish
  • CORE CASE HEATING FOR GAS TURBINE ENGINES
    Publication number: 20160169034
    Abstract: A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.
    Type: Application
    Filed: December 15, 2015
    Publication date: June 16, 2016
    Inventors: Steven Clarkson, Daniel K. Van Ness, II, Paul Thomas Rembish
  • GAS TURBINE ENGINES WITH HEATED CASES
    Publication number: 20160169036
    Abstract: A case for a gas turbine engine includes a case body defining an axially extending core flow path, a radially extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A lubricant conduit is connected to the case body and is in thermal communication with the structure-supporting member.
    Type: Application
    Filed: December 15, 2015
    Publication date: June 16, 2016
    Inventors: Steven Clarkson, Daniel K. Van Ness, II, Paul Thomas Rembish
  • System and method to improve the exhaust pressure across a RAM air turbine through secondary flow mixing
    Patent number: 8794902
    Abstract: A secondary flow lobe mixer increases the total-to-static pressure ratio across a Ram Air Turbine (RAT) by developing a localized pressure drop near the discharge of the turbine rotor exhaust. This pressure drop allows for additional power generation for a given free-stream flight condition.
    Type: Grant
    Filed: January 26, 2010
    Date of Patent: August 5, 2014
    Inventors: Daniel K. Van Ness, II, Brian E. Tews, Christian O. Rodriguez
  • Enhanced system and method to increase the total-to-static pressure ratio across a RAM air turbine using surface contoured flow agitators
    Patent number: 8480361
    Abstract: The total-to-static pressure ratio is increased across a Ram Air Turbine (RAT) by developing a localized accelerated flow of free-stream air near the discharge of the turbine rotor exhaust. This localized accelerated flow decreases the static pressure at the exit of the turbine and allows for additional power generation for a given free-stream flight condition. Lobe mixers in various locations improves mixing between the accelerated flow and the turbine exhaust flow, and the combined exhaust flow and the free-stream air surrounding the aerodynamic body.
    Type: Grant
    Filed: January 26, 2010
    Date of Patent: July 9, 2013
    Assignee: Mainstream Engineering Corporation
    Inventors: Brian E. Tews, Daniel K. Van Ness, II, Christian O. Rodriguez