Patents by Inventor Richard J. Musiol

Richard J. Musiol 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).

  • Modular enclosure with angled heat sink fins
    Patent number: 10080311
    Abstract: An apparatus and a system including the apparatus. The apparatus may include a modular electronics enclosure. The modular electronics enclosure may be configured to house an electronics device. The modular electronics enclosure may include a side portion. The modular electronics enclosure may further include angled external heat sink fins extending from the side portion.
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: September 18, 2018
    Assignee: Rockwell Collins, Inc.
    Inventor: Richard J. Musiol
  • Combustor hot streak alignment for gas turbine engine
    Patent number: 6554562
    Abstract: A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.
    Type: Grant
    Filed: June 15, 2001
    Date of Patent: April 29, 2003
    Assignee: Honeywell International, Inc.
    Inventors: Rodolphe Dudebout, Mark C. Morris, Douglas P. Freiberg, Craig W. McKeever, Richard J. Musiol, Ardeshir Riahi, William J. Howe
  • COMBUSTOR HOT STREAK ALIGNMENT FOR GAS TURBINE ENGINE
    Publication number: 20030002975
    Abstract: A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.
    Type: Application
    Filed: June 15, 2001
    Publication date: January 2, 2003
    Applicant: Honeywell International, Inc.
    Inventors: Rodolphe Dudebout, Mark C. Morris, Douglas P. Freiberg, Craig W. McKeever, Richard J. Musiol, Ardeshir Riahi, William J. Howe