Patents by Inventor Richard Whitton

Richard Whitton 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).

  • Patent number: 8096343
    Abstract: In precision casting of metallic components with very thin passage ducts, in particular turbine blades, by the lost-wax process, the ceramic core pins provided for forming the passage ducts are covered and stabilized via a low-melting reinforcing coat prior to injection of the wax material required for forming the wax pattern for the production of the ceramic casting mold, with the low-melting reinforcing coat being melted out together with the wax material after the casting mold has been formed on. The ceramic core pins are therefore not damaged during the production of the wax pattern, enabling very thin passage ducts to be formed in the precision casting process.
    Type: Grant
    Filed: March 7, 2008
    Date of Patent: January 17, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Richard Whitton
  • Patent number: 7874803
    Abstract: On a gas turbine rotor with internally cooled airfoils (4) of the turbine rotor blades and a mechanical sealing and damping element arranged between opposite side faces (6) of adjacent blade platforms (7), the gap is additionally aerodynamically sealed against the hot gas flow, by cooling air supplied from a cavity (5) of the airfoils via a cooling duct (9) into the gap between the side faces (6).
    Type: Grant
    Filed: July 27, 2005
    Date of Patent: January 25, 2011
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Richard Whitton
  • Publication number: 20090136350
    Abstract: With a gas-turbine engine, a sealing and damping element (9), which is loosely held between two adjacent platforms (6a, 6b) of turbine blades attached to a rotor disk, generally has a cross-section in the form of a straight three sided prism corresponding to an equilateral triangle, however with convex rubbing surface sides. Due to small swiveling movements enabled by the curvature of the sides, an increased rubbing and wear area is created during operation, which is adapted to the blade geometry and can be determined in advance, thus increasing damping and sealing efficiency.
    Type: Application
    Filed: September 4, 2007
    Publication date: May 28, 2009
    Inventor: Richard Whitton
  • Publication number: 20080216983
    Abstract: In precision casting of metallic components with very thin passage ducts, in particular turbine blades, by the lost-wax process, the ceramic core pins provided for forming the passage ducts are covered and stabilised via a low-melting reinforcing coat prior to injection of the wax material required for forming the wax pattern for the production of the ceramic casting mold, with the low-melting reinforcing coat being melted out together with the wax material after the casting mold has been formed on. The ceramic core pins are therefore not damaged during the production of the wax pattern, enabling very thin passage ducts to be formed in the precision casting process.
    Type: Application
    Filed: March 7, 2008
    Publication date: September 11, 2008
    Inventor: Richard Whitton
  • Publication number: 20080219855
    Abstract: A turbine blade, in the blade root (2) of which a curved and converging micro-turbine nozzle is provided, includes a passage duct (6) with large diameter originating at a cooling-air chamber (3) in the blade root, with a separately prefabricated micro-turbine nozzle element (7) with minimized flow cross-section, that is variably adaptable in size to the respective operating conditions, being fitted into said passage duct (6). Due to the reducible air mass flow that is adaptable to the actual requirements in the space between the turbine rotor wheels, air losses are reduced and efficiency is enhanced.
    Type: Application
    Filed: March 7, 2008
    Publication date: September 11, 2008
    Inventor: Richard Whitton
  • Publication number: 20060024166
    Abstract: On a gas turbine rotor with internally cooled airfoils (4) of the turbine rotor blades and a mechanical sealing and damping element arranged between opposite side faces (6) of adjacent blade platforms (7), the gap is additionally aerodynamically sealed against the hot gas flow, by cooling air supplied from a cavity (5) of the airfoils via a cooling duct (9) into the gap between the side faces (6).
    Type: Application
    Filed: July 27, 2005
    Publication date: February 2, 2006
    Inventor: Richard Whitton