Patents by Inventor Daniel K. Van Ness

Daniel K. Van Ness 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).

  • Acoustic liner with non-uniform volumetric distribution
    Patent number: 11339720
    Abstract: Disclosed is an acoustic liner for a gas turbine engine, having: a face sheet; a first plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the first plurality of resonator chamber cavities defining a first aggregated volume that is configured to target noise attenuation at a first frequency, the first plurality of resonator chamber cavities include first and second resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other; and a second plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the second plurality of resonator chamber cavities define a second aggregated volume that differs from the first aggregated volume and is configured to target noise attenuation at a second frequency, the second plurality of resonator chamber cavities include third and fourth resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each
    Type: Grant
    Filed: April 30, 2020
    Date of Patent: May 24, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Daniel K. Van Ness, Anthony R. Bifulco, David A. Topol, David A. Knaul, Michael Raymond LaFavor
  • ACOUSTIC LINER WITH NON-UNIFORM VOLUMETRIC DISTRIBUTION
    Publication number: 20210277829
    Abstract: Disclosed is an acoustic liner for a gas turbine engine, having: a face sheet; a first plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the first plurality of resonator chamber cavities defining a first aggregated volume that is configured to target noise attenuation at a first frequency, the first plurality of resonator chamber cavities include first and second resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other; and a second plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the second plurality of resonator chamber cavities define a second aggregated volume that differs from the first aggregated volume and is configured to target noise attenuation at a second frequency, the second plurality of resonator chamber cavities include third and fourth resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each
    Type: Application
    Filed: April 30, 2020
    Publication date: September 9, 2021
    Inventors: Daniel K. Van Ness, Anthony R. Bifulco, David A. Topol, David A. Knaul, Michael Raymond LaFavor
  • Incidence-tolerant, high-turning fan exit stator
    Patent number: 10060263
    Abstract: A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge, an outer diameter edge, a trailing edge and a leading edge. The leading edge has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge. The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction.
    Type: Grant
    Filed: August 14, 2015
    Date of Patent: August 28, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel K. Van Ness, Mark A. Stephens, Edward J. Gallagher, Joseph C. Straccia, Vikram A. Kumar
  • INCIDENCE-TOLERANT, HIGH-TURNING FAN EXIT STATOR
    Publication number: 20160076380
    Abstract: A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge, an outer diameter edge, a trailing edge and a leading edge. The leading edge has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge. The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction.
    Type: Application
    Filed: August 14, 2015
    Publication date: March 17, 2016
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel K. Van Ness, Mark A. Stephens, Edward J. Gallagher, Joseph C. Straccia, Vikram A. Kumar