Patents by Inventor James S. Perron

James S. Perron 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: 20150308273
    Abstract: A turbine engine component for a gas turbine engine includes an inner disk, an outer shroud, and a plurality of blades. Each blade comprises a blade root and an airfoil body. The blade root is plated at least in part with a noble metal, and is coupled to the inner disk. The airfoil body extends at least partially between the blade root and the outer shroud.
    Type: Application
    Filed: November 14, 2014
    Publication date: October 29, 2015
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: James S. Perron, William C. Baker, Derek A. Rice
  • Patent number: 7832986
    Abstract: A dual alloy turbine rotor is provided and includes an integrally formed blade ring and a disk. The blade ring is made of a first alloy and includes a ring portion and a plurality of airfoils extending therefrom, where the ring portion includes an inner surface, and each airfoil includes an internal cavity formed therein. The disk is made of a second alloy and may have a beveled outer peripheral surface. The disk is disposed within the ring portion such that the disk outer peripheral surface contacts at least a portion of the ring portion inner surface. Methods of manufacturing the turbine rotor are also provided.
    Type: Grant
    Filed: March 7, 2007
    Date of Patent: November 16, 2010
    Assignee: Honeywell International Inc.
    Inventors: William C. Baker, Thomas E. Strangman, Derek A. Rice, James S. Perron, Christopher Zollars
  • Publication number: 20090068016
    Abstract: A turbine engine component for a gas turbine engine includes an inner disk, an outer shroud, and a plurality of blades. Each blade comprises a blade root and an airfoil body. The blade root is plated at least in part with a noble metal, and is coupled to the inner disk. The airfoil body extends at least partially between the blade root and the outer shroud.
    Type: Application
    Filed: April 20, 2007
    Publication date: March 12, 2009
    Applicant: HONEYWELL INTERNATIONAL, INC.
    Inventors: James S. Perron, William C. Baker, Derek A. Rice
  • Publication number: 20080219853
    Abstract: A dual alloy turbine rotor is provided and includes an integrally formed blade ring and a disk. The blade ring is made of a first alloy and includes a ring portion and a plurality of airfoils extending therefrom, where the ring portion includes an inner surface, and each airfoil includes an internal cavity formed therein. The disk is made of a second alloy and may have a beveled outer peripheral surface. The disk is disposed within the ring portion such that the disk outer peripheral surface contacts at least a portion of the ring portion inner surface. Methods of manufacturing the turbine rotor are also provided.
    Type: Application
    Filed: March 7, 2007
    Publication date: September 11, 2008
    Inventors: William C. Baker, Thomas E. Strangman, Derek A. Rice, James S. Perron, Christopher Zollars
  • Patent number: 5465780
    Abstract: A method is disclosed for producing a hollow airfoil, specifically, a blade or vane for a gas turbine engine, which is formed with a complex interior for cooling purposes. Broadly, the method comprises the steps of molding a green ceramic core having outer surfaces generally contoured to produce the intended interior surfaces of the completed airfoil, heating the green ceramic core to a sufficient extent to produce a fired core, and operating on the fired core with a laser to modify the characteristics of the fired core. Use of the laser enables the formation of detailed features having a transverse dimension less than approximately 0.020 inches. Specific operations may include labeling, trimming, cutting, drilling either by punching or trepanning, etching or milling, and glazing or strengthening. In another embodiment of the invention, a layer is produced on the core surface having a very high surface energy to promote the flow of the casting alloy around the core within the mold.
    Type: Grant
    Filed: November 23, 1993
    Date of Patent: November 14, 1995
    Assignee: AlliedSignal Inc.
    Inventors: Michael S. Muntner, James S. Perron
  • Patent number: 4244551
    Abstract: Composite ceramic shell molds for investment casting and subsequent directional solidification of nickel and cobalt base superalloys is described. The composite ceramic shell mold is composed of an inner component having an alumina content of at least 80 percent and an average thickness of about ten mils and an outer layer composed predominantly of zircon having a thickness of from 0.1 to 0.4 inches. The alumina component of the shell mold is wet by the superalloy material and this wetting action is believed to cause the substantial elimination of a surface defect problem known as chain porosity. The zircon component of the shell mold had desirable mechanical properties and may easily be removed from the solidified casting. The alumina and zircon components are bonded together in such a fashion that they will not separate during the casting process.
    Type: Grant
    Filed: June 30, 1978
    Date of Patent: January 13, 1981
    Assignee: United Technologies Corporation
    Inventors: Bruce E. Terkelsen, Michael Cybulsky, James S. Perron
  • Patent number: 3981346
    Abstract: In making columnar grained castings the shell mold is spaced from the chill plate by a ceramic ring on which the mold is positioned, the ring being made thicker and/or of a different ceramic from the mold to withstand the thermal stress developing while the mold is being heated for pouring, so that the mold, not being subjected to such stresses at the base, may be made thinner for producing better castings. In this way the best mold material for the purpose may be selected, as, for example, a material to have no reaction with the alloy and, by lowering the thermal gradient decrease the likelihood of mold failure.
    Type: Grant
    Filed: October 3, 1974
    Date of Patent: September 21, 1976
    Assignee: United Technologies Corporation
    Inventors: Douglas R. Hayes, James S. Perron
  • Patent number: 3933190
    Abstract: A method for producing shell molds for the investment casting and subsequent directional solidification of nickel and cobalt based superalloys is described. The shell mold is composed of high purity alumina and characterized by the presence of silica in trace form only. The shell mold of the present invention is nonreactive with molten nickel and cobalt base superalloys even during exposures of up to 12 hours. Additionally the alumina shell mold of the present invention has a unique combination of mechanical strength and stability at elevated temperatures.
    Type: Grant
    Filed: December 16, 1974
    Date of Patent: January 20, 1976
    Assignee: United Technologies Corporation
    Inventors: Michael H. Fassler, James S. Perron