Patents by Inventor Rodney D. Conrad

Rodney D. Conrad 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).

  • Attachment of piloting feature
    Patent number: 11193375
    Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.
    Type: Grant
    Filed: November 5, 2019
    Date of Patent: December 7, 2021
    Assignee: Rolls-Royce Corporation
    Inventors: Patrick E. Bailey, Samuel J. Lacombe, Eric W. Engebretsen, Rodney D. Conrad, Matthew J. Kappes
  • ATTACHMENT OF PILOTING FEATURE
    Publication number: 20200063563
    Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.
    Type: Application
    Filed: November 5, 2019
    Publication date: February 27, 2020
    Inventors: Patrick E. Bailey, Samuel J. Lacombe, Eric W. Engebretsen, Rodney D. Conrad, Matthew J. Kappes
  • Attachment of piloting feature
    Patent number: 10480321
    Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.
    Type: Grant
    Filed: November 18, 2015
    Date of Patent: November 19, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Patrick E. Bailey, Samuel J. Lacombe, Eric W. Engebretsen, Rodney D. Conrad, Matthew J. Kappes
  • ATTACHMENT OF PILOTING FEATURE
    Publication number: 20160160688
    Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.
    Type: Application
    Filed: November 18, 2015
    Publication date: June 9, 2016
    Inventors: Patrick E. Bailey, Samuel J. Lacombe, Eric W. Engebretsen, Rodney D. Conrad, Matthew J. Kappes
  • Vane arrangement and a method of making vane arrangement
    Patent number: 7837444
    Abstract: Within gas turbine engines 10 it is necessary to provide fixed vanes which comprise an aerofoil in the gas flow through the gas turbine engine 10. These vanes are subject to significant stressing. Therefore it is generally necessary to secure the vane at one end 103 through an appropriate bond such as brazing while at another end a friction damping response is achieved. By providing an anti-bonding layer it is possible to prevent a mechanical bond being formed at the friction damping end 105. Furthermore, a tight fit can be emphasized by residual bonding material remaining after an attempted bonding process upon the anti-bonding layer.
    Type: Grant
    Filed: November 16, 2006
    Date of Patent: November 23, 2010
    Assignee: Rolls-Royce PLC
    Inventor: Rodney D. Conrad
  • Vane arrangement and a method of making vane arrangement
    Publication number: 20070140854
    Abstract: Within gas turbine engines 10 it is necessary to provide fixed vanes which comprise an aerofoil in the gas flow through the gas turbine engine 10. These vanes are subject to significant stressing. Therefore it is generally necessary to secure the vane at one end 103 through an appropriate bond such as brazing whilst at another end a friction damping response is achieved. By providing an anti-bonding layer it is possible to prevent a mechanical bond being formed at the friction damping end 105. Furthermore, a tight fit can be emphasised by residual bonding material remaining after an attempted bonding process upon the anti-bonding layer.
    Type: Application
    Filed: November 16, 2006
    Publication date: June 21, 2007
    Applicant: ROLLS-ROYCE PLC
    Inventor: Rodney D. Conrad