Patents by Inventor Myron KLEIN

Myron KLEIN 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).

  • Compressor rotor for supersonic flutter and/or resonant stress mitigation
    Patent number: 11353038
    Abstract: The gas turbine compressor for an aircraft gas turbine engine includes a compressor rotor having a plurality of compressor blades circumferentially distributed around a hub. Each of the compressor blades has an airfoil extending radially outward from the hub to a blade tip. A circumferential row of the compressor blades includes two or more different blade types, at least one modified blade of the two or more different blade types having means for generating different shock patterns between adjacent ones of the two or more different blade types when the gas turbine compressor operates in supersonic flow regimes. The means for generating different shock patterns on the modified blade aerodynamically mistune the two or more different blade types.
    Type: Grant
    Filed: April 29, 2020
    Date of Patent: June 7, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ignatius Theratil, Krishna Prasad Balike, Aldo Abate, Sean Kelly, Peter Townsend, Ronald Dutton, Anthony Brown, Paul Stone, Myron Klein, Milica Kojovic, Robert Venditti
  • COMPRESSOR ROTOR FOR SUPERSONIC FLUTTER AND/OR RESONANT STRESS MITIGATION
    Publication number: 20200392968
    Abstract: The gas turbine compressor for an aircraft gas turbine engine includes a compressor rotor having a plurality of compressor blades circumferentially distributed around a hub. Each of the compressor blades has an airfoil extending radially outward from the hub to a blade tip. A circumferential row of the compressor blades includes two or more different blade types, at least one modified blade of the two or more different blade types having means for generating different shock patterns between adjacent ones of the two or more different blade types when the gas turbine compressor operates in supersonic flow regimes. The means for generating different shock patterns on the modified blade aerodynamically mistune the two or more different blade types.
    Type: Application
    Filed: April 29, 2020
    Publication date: December 17, 2020
    Inventors: Ignatius THERATIL, Krishna Prasad BALIKE, Aldo ABATE, Sean KELLY, Peter TOWNSEND, Ronald DUTTON, Anthony BROWN, Paul STONE, Myron KLEIN, Milica KOJOVIC, Robert VENDITTI
  • Compressor rotor for supersonic flutter and/or resonant stress mitigation
    Patent number: 10670041
    Abstract: A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.
    Type: Grant
    Filed: February 17, 2017
    Date of Patent: June 2, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ignatius Theratil, Krishna Prasad Balike, Aldo Abate, Sean Kelly, Peter Townsend, Ronald Dutton, Anthony Brown, Paul Stone, Myron Klein, Milica Kojovic, Robert Venditti
  • COMPRESSOR ROTOR FOR SUPERSONIC FLUTTER AND/OR RESONANT STRESS MITIGATION
    Publication number: 20170241432
    Abstract: A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.
    Type: Application
    Filed: February 17, 2017
    Publication date: August 24, 2017
    Inventors: Ignatius THERATIL, Krishna Prasad BALIKE, Aldo ABATE, Sean KELLY, Peter TOWNSEND, Ronald DUTTON, Anthony BROWN, Paul STONE, Myron KLEIN, Milica KOJOVIC, Robert VENDITTI