Patents by Inventor Donald E. Pinnick

Donald E. Pinnick 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).

  • Gas turbine engine variable porosity combustor liner
    Patent number: 10203115
    Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.
    Type: Grant
    Filed: June 20, 2017
    Date of Patent: February 12, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Donald E. Pinnick, Kenneth W. Froemming, Bruce E. Varney
  • Combustor with spring-loaded crossover tubes
    Patent number: 10161635
    Abstract: Crossover tubes for use with cans of a turbine engine. The crossover tubes include an outer member, an inner member that is adapted to move collinearly with the outer member. The crossover tubes also include a pair of flanges and a biasing member positioned between the flanges.
    Type: Grant
    Filed: April 8, 2015
    Date of Patent: December 25, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: Donald E. Pinnick, Kevin M. Sauer, Russell N. Bennett, Bradley A. Lemke, Caleb Camara, Catherine Hidlebaugh, Kathryn M. Dimon
  • Gas turbine engine with improved combustion liner
    Patent number: 9879861
    Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.
    Type: Grant
    Filed: December 27, 2013
    Date of Patent: January 30, 2018
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Donald E. Pinnick, Kenneth W. Froemming, Bruce E. Varney, James C. Loebig, Todd Taylor
  • GAS TURBINE ENGINE VARIABLE POROSITY COMBUSTOR LINER
    Publication number: 20170292703
    Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.
    Type: Application
    Filed: June 20, 2017
    Publication date: October 12, 2017
    Applicants: Rolls-Royce Corporation, Rolls-Royce Corporation
    Inventors: Donald E. Pinnick, Kenneth W. Froemming, Bruce E. Varney
  • Gas turbine engine variable porosity combustor liner
    Patent number: 9719684
    Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.
    Type: Grant
    Filed: December 20, 2013
    Date of Patent: August 1, 2017
    Assignees: Rolls-Royce North America Technologies, Inc., Rolls-Royce Corporation
    Inventors: Donald E. Pinnick, Kenneth W. Froemming, Bruce E. Varney
  • COMBUSTOR WITH SPRING-LOADED CROSSOVER TUBES
    Publication number: 20160010868
    Abstract: Crossover tubes for use with cans of a turbine engine. The crossover tubes include an outer member, an inner member that is adapted to move collinearly with the outer member. The crossover tubes also include a pair of flanges and a biasing member positioned between the flanges.
    Type: Application
    Filed: April 8, 2015
    Publication date: January 14, 2016
    Inventors: Donald E. Pinnick, Kevin M. Sauer, Russell N. Bennett, Bradley A. Lemke, Caleb Camara, Catherine Hidlebaugh, Katherine A. Dimon
  • GAS TURBINE ENGINE COMBUSTOR LINER
    Publication number: 20150013340
    Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.
    Type: Application
    Filed: December 27, 2013
    Publication date: January 15, 2015
    Applicants: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Donald E. Pinnick, Kenneth W. Froemming, Bruce E. Varney, James C. Loebig, Todd Taylor
  • GAS TURBINE ENGINE COMBUSTOR LINER
    Publication number: 20140260282
    Abstract: A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.
    Type: Application
    Filed: December 20, 2013
    Publication date: September 18, 2014
    Applicants: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Donald E. Pinnick, Kenneth W. Froemming, Bruce E. Varney