Patents by Inventor Veeraraghava Raju Hasti

Veeraraghava Raju Hasti 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).

  • Reverse-flow annular combustor for reduced emissions
    Patent number: 9400110
    Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.
    Type: Grant
    Filed: October 19, 2012
    Date of Patent: July 26, 2016
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Rodolphe Dudebout, Terrel Kuhn, Vinayender Kuchana, Veeraraghava Raju Hasti, Raymond Gage, Sunil James
  • REVERSE-FLOW ANNULAR COMBUSTOR FOR REDUCED EMISSIONS
    Publication number: 20140109581
    Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.
    Type: Application
    Filed: October 19, 2012
    Publication date: April 24, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Rodolphe Dudebout, Terrel Kuhn, Vinayender Kuchana, Veeraraghava Raju Hasti, Raymond Gage, Sunil James
  • REVERSE-FLOW ANNULAR COMBUSTOR FOR REDUCED EMISSIONS
    Publication number: 20120304647
    Abstract: A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.
    Type: Application
    Filed: June 6, 2011
    Publication date: December 6, 2012
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Rodolphe Dudebout, Veeraraghava Raju Hasti, Terrel Kuhn, Sunil James, Mario Scaini