Patents by Inventor Muthuvel Murugan

Muthuvel Murugan 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).

  • Adaptable articulating axial-flow compressor/turbine rotor blade
    Patent number: 11073160
    Abstract: Conventional gas turbine engines are generally optimized to operate at nearly a fixed speed with fixed blade geometries for the design operating condition. When the operating condition of the engine changes, the flow incidence angles may not be optimum with the blade geometries resulting in reduced off-design performance. By contrast, according to embodiments of the present invention, articulating the pitch angle of turbine blades in coordination with adjustable nozzle vanes improves performance by maintaining flow incidence angles within the optimum range at all operating conditions of a gas turbine engine. Maintaining flow incidence angles within the optimum range can prevent the likelihood of flow separation in the blade passage and also reduce the thermal stresses developed due to aerothermal loads for variable speed gas turbine applications.
    Type: Grant
    Filed: August 31, 2017
    Date of Patent: July 27, 2021
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventors: Muthuvel Murugan, Anindya Ghoshal, Luis Bravo
  • FUNCTIONALLY GRADED SANDPHOBIC BLENDED COMPOSITE COATINGS
    Publication number: 20210222626
    Abstract: A thermal barrier coating (TBC) material includes calcic-magnesia-alumina-silicates-resistant rare-earth (RE) oxide powder blended with yttria-stabilized zirconia (YSZ). The RE oxide powder may include any of gadolinium oxide, samarium oxide, ytterbium oxide and cerium oxide. The RE oxide powder may include gadolinium zirconate (GZO).
    Type: Application
    Filed: January 22, 2020
    Publication date: July 22, 2021
    Inventors: Andy Nieto, Michael J. Walock, Anindya Ghoshal, Blake D. Barnett, Clara M. Mock, Mark L. Graybeal, Marc S. Pepi, Muthuvel Murugan
  • ADAPTABLE ARTICULATING AXIAL-FLOW COMPRESSOR/TURBINE ROTOR BLADE
    Publication number: 20180066671
    Abstract: Conventional gas turbine engines are generally optimized to operate at nearly a fixed speed with fixed blade geometries for the design operating condition. When the operating condition of the engine changes, the flow incidence angles may not be optimum with the blade geometries resulting in reduced off-design performance. By contrast, according to embodiments of the present invention, articulating the pitch angle of turbine blades in coordination with adjustable nozzle vanes improves performance by maintaining flow incidence angles within the optimum range at all operating conditions of a gas turbine engine. Maintaining flow incidence angles within the optimum range can prevent the likelihood of flow separation in the blade passage and also reduce the thermal stresses developed due to aerothermal loads for variable speed gas turbine applications.
    Type: Application
    Filed: August 31, 2017
    Publication date: March 8, 2018
    Inventors: Muthuvel Murugan, Anindya Ghoshal, Luis Bravo