Patents by Inventor Yu Xie Mukherjee

Yu Xie Mukherjee 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).

  • Airfoil tip geometry to reduce blade wear in gas turbine engines
    Patent number: 10633983
    Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge, the leading edge and the trailing edge define a chord distance. The airfoil includes a tip portion extending between the pressure sidewall and the suction sidewall. The tip portion includes a planar section and a recessed section. The recessed section extends adjacent to the planar section such that a thickness of the planar section is less than a thickness of the airfoil. The recessed section is offset a predetermined distance from the leading edge and the trailing edge along the chord distance.
    Type: Grant
    Filed: March 7, 2016
    Date of Patent: April 28, 2020
    Assignee: General Electric Company
    Inventors: Ananda Barua, Neelesh Nandkumar Sarawate, Kenneth Martin Lewis, Changjie Sun, Yu Xie Mukherjee, Sathyanarayanan Raghavan
  • Method and apparatus for active clearance control for high pressure compressors using fan/booster exhaust air
    Patent number: 10087772
    Abstract: The turbomachine includes a rotatable member defining an axis of rotation and an inner annular casing extending circumferentially over at least a portion of the rotatable member. The inner annular casing includes a radially outer surface. The turbomachine further includes an outer annular casing extending over at least a portion of the inner annular casing. The inner annular casing and the outer annular casing define a plurality of cavities therebetween. The clearance control system includes a manifold system including a plurality of conduits extending circumferentially about the inner annular casing and disposed within the cavities. The clearance control system also includes an impingement system extending circumferentially about the inner annular casing and disposed within the cavities. The conduits are configured to channel a flow of cooling fluid to the impingement system which is configured to channel the cooling fluid to the radially outer surface of the inner annular casing.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: October 2, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Changjie Sun, Yu Xie Mukherjee, Bhaskar Nanda Mondal, Atanu Saha, Marcia Boyle Johnson, Wenfeng Lu
  • AIRFOIL TIP GEOMETRY TO REDUCE BLADE WEAR IN GAS TURBINE ENGINES
    Publication number: 20170254210
    Abstract: An airfoil for use in a turbomachine includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge, the leading edge and the trailing edge define a chord distance. The airfoil includes a tip portion extending between the pressure sidewall and the suction sidewall. The tip portion includes a planar section and a recessed section. The recessed section extends adjacent to the planar section such that a thickness of the planar section is less than a thickness of the airfoil. The recessed section is offset a predetermined distance from the leading edge and the trailing edge along the chord distance.
    Type: Application
    Filed: March 7, 2016
    Publication date: September 7, 2017
    Inventors: Ananda Barua, Neelesh Nandkumar Sarawate, Kenneth Martin Lewis, Changjie Sun, Yu Xie Mukherjee, Sathyanarayanan Raghavan
  • METHOD AND APPARATUS FOR ACTIVE CLEARANCE CONTROL FOR HIGH PRESSURE COMPRESSORS USING FAN/BOOSTER EXHAUST AIR
    Publication number: 20170175769
    Abstract: The turbomachine includes a rotatable member defining an axis of rotation and an inner annular casing extending circumferentially over at least a portion of the rotatable member. The inner annular casing includes a radially outer surface. The turbomachine further includes an outer annular casing extending over at least a portion of the inner annular casing. The inner annular casing and the outer annular casing define a plurality of cavities therebetween. The clearance control system includes a manifold system including a plurality of conduits extending circumferentially about the inner annular casing and disposed within the cavities. The clearance control system also includes an impingement system extending circumferentially about the inner annular casing and disposed within the cavities. The conduits are configured to channel a flow of cooling fluid to the impingement system which is configured to channel the cooling fluid to the radially outer surface of the inner annular casing.
    Type: Application
    Filed: December 21, 2015
    Publication date: June 22, 2017
    Inventors: Changjie Sun, Yu Xie Mukherjee, Bhaskar Nanda Mondal, Atanu Saha, Marcia Boyle Johnson, Wenfeng Lu