Patents by Inventor Anand Roday

Anand Roday 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 with a diffuser cavity cooled compressor
    Patent number: 11377957
    Abstract: A gas turbine engine includes a compressor section having a high pressure compressor, the high pressure compressor including an aft-most compressor stage. The gas turbine engine also includes a combustion section having a stage of discharge nozzles, the stage of discharge nozzles located downstream of the aft-most compressor stage and upstream of a diffuser cavity. The gas turbine engine also includes a high pressure spool drivingly coupled to the high pressure compressor, the high pressure spool forming in part a compressor discharge pressure seal and including a forward spool section. The forward spool section extends between the compressor discharge pressure seal and the aft-most compressor stage, the forward spool section defining an airflow cavity for providing a cooling airflow from the diffuser cavity to the aft-most compressor stage.
    Type: Grant
    Filed: May 9, 2017
    Date of Patent: July 5, 2022
    Assignee: General Electric Company
    Inventors: Alan Glenn Turner, Monty Lee Shelton, Anand Roday, Aigbedion Akwara
  • GAS TURBINE ENGINE WITH A COOLED COMPRESSOR
    Publication number: 20180328177
    Abstract: A gas turbine engine includes a compressor section having a high pressure compressor, the high pressure compressor including an aft-most compressor stage. The gas turbine engine also includes a combustion section having a stage of discharge nozzles, the stage of discharge nozzles located downstream of the aft-most compressor stage and upstream of a diffuser cavity. The gas turbine engine also includes a high pressure spool drivingly coupled to the high pressure compressor, the high pressure spool forming in part a compressor discharge pressure seal and including a forward spool section. The forward spool section extends between the compressor discharge pressure seal and the aft-most compressor stage, the forward spool section defining an airflow cavity for providing a cooling airflow from the diffuser cavity to the aft-most compressor stage.
    Type: Application
    Filed: May 9, 2017
    Publication date: November 15, 2018
    Inventors: Alan Glenn Turner, Monty Lee Shelton, Anand Roday, Aigbedion Akwara