Patents by Inventor Srinivas Jaya Chunduru

Srinivas Jaya Chunduru 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).

  • Structured light measuring apparatus and methods
    Patent number: 10295436
    Abstract: A field deployable, portable structured light measurement (SLM) apparatus, together with a structured light measurement process to manage part to part variation in production and in the field, to support both rotor airfoil mistuning and rotor airfoil repair limits.
    Type: Grant
    Filed: March 17, 2016
    Date of Patent: May 21, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Richard David Conner, Bruce David Reynolds, Jonathan C. Bittner, Srinivas Jaya Chunduru, Bruce D. Wilson
  • STRUCTURED LIGHT MEASURING APPARATUS AND METHODS
    Publication number: 20170268963
    Abstract: A field deployable, portable structured light measurement (SLM) apparatus, together with a structured light measurement process to manage part to part variation in production and in the field, to support both rotor airfoil mistuning and rotor airfoil repair limits.
    Type: Application
    Filed: March 17, 2016
    Publication date: September 21, 2017
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Richard David Conner, Bruce David Reynolds, Jonathan C. Bittner, Srinivas Jaya Chunduru, Bruce D. Wilson
  • Gas turbine engine cooling systems having hub-bleed impellers and methods for the production thereof
    Patent number: 8920128
    Abstract: Embodiments of a gas turbine engine cooling system for deployment within a gas turbine engine are provided, as are embodiment of a method for producing a gas turbine engine cooling system. In one embodiment, the gas turbine engine cooling system includes an impeller having a hub, a plurality of hub bleed air passages, and a central bleed air conduit. The plurality of hub bleed air passages each have an inlet formed in an outer circumferential surface of the hub and an outlet formed in an inner circumferential surface of the hub. The central bleed air conduit is fluidly coupled to the outlets of the plurality of hub bleed air passages and is configured to conduct bleed air discharged by the plurality of hub bleed air passages to a section of the gas turbine engine downstream of the impeller to provide cooling air thereto.
    Type: Grant
    Filed: October 19, 2011
    Date of Patent: December 30, 2014
    Assignee: Honeywell International Inc.
    Inventors: Mark Matwey, David K. Jan, Srinivas Jaya Chunduru
  • GAS TURBINE ENGINE COOLING SYSTEMS HAVING HUB-BLEED IMPELLERS AND METHODS FOR THE PRODUCTION THEREOF
    Publication number: 20130098061
    Abstract: Embodiments of a gas turbine engine cooling system for deployment within a gas turbine engine are provided, as are embodiment of a method for producing a gas turbine engine cooling system. In one embodiment, the gas turbine engine cooling system includes an impeller having a hub, a plurality of hub bleed air passages, and a central bleed air conduit. The plurality of hub bleed air passages each have an inlet formed in an outer circumferential surface of the hub and an outlet formed in an inner circumferential surface of the hub. The central bleed air conduit is fluidly coupled to the outlets of the plurality of hub bleed air passages and is configured to conduct bleed air discharged by the plurality of hub bleed air passages to a section of the gas turbine engine downstream of the impeller to provide cooling air thereto.
    Type: Application
    Filed: October 19, 2011
    Publication date: April 25, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Mark Matwey, David K. Jan, Srinivas Jaya Chunduru