Patents by Inventor Kurt A Hassett

Kurt A Hassett 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).

  • Systems and methods for performing cooling airflow analysis of gas turbine engine components
    Patent number: 7685870
    Abstract: Systems and methods for performing cooling airflow analysis of gas turbine engine components are provided. In this regard, a representative system includes an airflow insert operative to form a seal with a component, the airflow insert having a main portion and a removable sacrificial portion, the sacrificial portion being sized and shaped to engage the component, the main portion having a cavity sized and shaped to removably receive the sacrificial portion, the main portion being sized and shaped to form a seal about the sacrificial portion and a corresponding portion of the component.
    Type: Grant
    Filed: September 27, 2007
    Date of Patent: March 30, 2010
    Assignee: United Technologies Corporation
    Inventors: Daniel E. Quinn, Kurt A. Hassett
  • Systems and methods for determining airflow parameters of gas turbine engine components
    Patent number: 7640793
    Abstract: Systems and methods for determining airflow parameters of gas turbine engine components are provided. In this regard, a representative method includes: receiving information from multiple test systems regarding a first airflow parameter of a gas turbine engine component; and using the information to establish a desired performance parameter that is to be exhibited by a repaired component.
    Type: Grant
    Filed: September 12, 2007
    Date of Patent: January 5, 2010
    Assignee: United Technologies Corporation
    Inventors: Thomas McCall, Kurt A Hassett
  • Systems and Methods for Performing Cooling Airflow Analysis of Gas Turbine Engine Components
    Publication number: 20090084170
    Abstract: Systems and methods for performing cooling airflow analysis of gas turbine engine components are provided. In this regard, a representative system includes an airflow insert operative to form a seal with a component, the airflow insert having a main portion and a removable sacrificial portion, the sacrificial portion being sized and shaped to engage the component, the main portion having a cavity sized and shaped to removably receive the sacrificial portion, the main portion being sized and shaped to form a seal about the sacrificial portion and a corresponding portion of the component.
    Type: Application
    Filed: September 27, 2007
    Publication date: April 2, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Daniel E. Quinn, Kurt A. Hassett
  • Systems and Methods for Determining Airflow Parameters of Gas Turbine Engine Components
    Publication number: 20090064773
    Abstract: Systems and methods for determining airflow parameters of gas turbine engine components are provided. In this regard, a representative method includes: receiving information from multiple test systems regarding a first airflow parameter of a gas turbine engine component; and using the information to establish a desired performance parameter that is to be exhibited by a repaired component.
    Type: Application
    Filed: September 12, 2007
    Publication date: March 12, 2009
    Applicant: UNITED TECHNOLOGIES CORP.
    Inventors: Thomas McCall, Kurt A. Hassett