Patents by Inventor Keshava B. Kumar

Keshava B. Kumar 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).

  • Publication number: 20100021286
    Abstract: A mid-turbine frame assembly includes a mid-turbine frame, a ring structure and a plurality of actuated struts. The ring structure surrounds the mid-turbine frame, and has an interior surface and an exterior surface. The actuated struts connect the ring structure to the mid-turbine frame. The actuated struts are strain actuated so that the actuated struts reposition the ring structure in response to a strain.
    Type: Application
    Filed: July 23, 2008
    Publication date: January 28, 2010
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nagendra Somanath, Keshava B. Kumar, Christopher M. Dye
  • Publication number: 20100008765
    Abstract: An expandable mid-turbine frame assembly includes a first bearing cone, a second bearing cone and a mid-turbine frame. The mid-turbine frame assembly connects to a gas turbine engine casing and transfers a first load from a first bearing and a second load from a second bearing towards the engine casing. The first bearing cone transfers the first load from the first bearing. The second bearing cone transfers the second load from the second bearing. The mid-turbine frame is connected to the first and second bearing cones and includes segments. Each segment includes a pre-stressed support for equilibrating the first and second loads.
    Type: Application
    Filed: September 18, 2009
    Publication date: January 14, 2010
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Somanath Nagendra, Keshava B. Kumar
  • Patent number: 7632064
    Abstract: A variable geometry inlet guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning inlet flow to a turbine or compressor and an internal spar spaced from the airfoil shell by an air gap. A number of actuation mechanisms grounded to the spar and connected to the inner surface of the aerodynamic shell adjust the shape of the shell in response to varying operating conditions of the engine, imbalanced aerodynamic loading of the shell or vibration or other transient loads on the shell.
    Type: Grant
    Filed: September 1, 2006
    Date of Patent: December 15, 2009
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar
  • Patent number: 7610763
    Abstract: A mid-turbine frame has a pre-stress design and is connected to an engine casing of a jet turbine engine to distribute a first load from a first bearing and a second load from a second bearing. The mid-turbine frame includes at least one torque box, a first bearing, a second bearing, and at least one strut. The torque box absorbs the first and second loads. The first bearing cone connects the first bearing to the torque box and the second bearing cone connects the second bearing to the torque box. The strut connects the torque box to the engine casing.
    Type: Grant
    Filed: May 9, 2006
    Date of Patent: November 3, 2009
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B . Kumar
  • Patent number: 7594404
    Abstract: An engine casing for a mid-turbine frame having a plurality of radially extending struts includes a ring structure and at least one mount. The ring structure has an interior surface, an exterior surface, and a plurality of equally spaced dimples along the exterior surface and protruding from the interior surface. The ring structure is connected to each of the plurality of struts at the interior surface at the dimples. The mount is positioned within each of the dimples and transfers load to the engine casing.
    Type: Grant
    Filed: July 27, 2006
    Date of Patent: September 29, 2009
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar, William A. Sowa
  • Patent number: 7594405
    Abstract: An engine casing assembly having dual load transfer points includes a U-shaped mid-turbine frame, an engine casing, a plurality of dimples, a strut and a mounting apparatus. The engine casing has an exterior surface and an interior surface. A plurality dimples are formed in the engine casing so that U-shaped protrusions are formed in the interior surface and U-shaped indentions are formed in the exterior surface. A strut connects one U-shaped protrusion to the mid-turbine frame and a mounting apparatus located within an indention so that a load is transferred from the mid-turbine frame to the engine casing and the mounting apparatus.
    Type: Grant
    Filed: July 23, 2008
    Date of Patent: September 29, 2009
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar, Christopher M. Dye, William A. Sowa
  • Publication number: 20090120102
    Abstract: The turbine engine assembly has a frame and a turbine engine spool. A strut couples the frame to the spool and an actuator couples the strut to the frame. The actuator has a spring.
    Type: Application
    Filed: November 13, 2007
    Publication date: May 14, 2009
    Inventors: Nagendra Somanath, Christopher M. Dye, Keshava B. Kumar
  • Publication number: 20080276621
    Abstract: An engine casing assembly having dual load transfer points includes a U-shaped mid-turbine frame, an engine casing, a plurality of dimples, a strut and a mounting apparatus. The engine casing has an exterior surface and an interior surface. A plurality dimples are formed in the engine casing so that U-shaped protrusions are formed in the interior surface and U-shaped indentions are formed in the exterior surface. A strut connects one U-shaped protrusion to the mid-turbine frame and a mounting apparatus located within an indention so that a load is transferred from the mid-turbine frame to the engine casing and the mounting apparatus.
    Type: Application
    Filed: July 23, 2008
    Publication date: November 13, 2008
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nagendra Somanath, Keshava B. Kumar, Christopher M. Dye, William A. Sowa
  • Publication number: 20080134687
    Abstract: A mid-turbine frame is connected to at least one mount of a gas turbine engine for transferring a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a first load structure, a second load structure, and a plurality of struts. The first load structure combines the first load and the second load into a combined load. The second load structure transfers the combined load to the mount. The struts are connected between the first load structure and the second load structure and transfers the combined load from the first load structure to the second load structure.
    Type: Application
    Filed: December 6, 2006
    Publication date: June 12, 2008
    Applicant: United Technologies Corporation
    Inventors: Keshava B. Kumar, Nagendra Somanath, William A. Sowa
  • Publication number: 20080134688
    Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a load transfer unit, a torque box rotatably positioned within the load transfer unit, and a plurality of struts. The load transfer unit has a first locking element and combines the first load and the second load into a combined load. The torque box has a second locking element that is engagable with the first locking element of the load transfer unit. The plurality of struts are connected between the torque box and the mount, and transfer the combined load from the torque box to the mount. The first locking element and the second locking element are at least one of a rib or a groove.
    Type: Application
    Filed: December 6, 2006
    Publication date: June 12, 2008
    Applicant: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar, William A. Sowa, Christopher Dye
  • Publication number: 20080056888
    Abstract: A guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning a flow of working fluid and an internal spar spaced from the aerodynamic shell by an air gap and reinforced by stiffeners.
    Type: Application
    Filed: September 1, 2006
    Publication date: March 6, 2008
    Applicant: United Technologies
    Inventors: Nagendra Somanath, Keshava B. Kumar
  • Publication number: 20080056904
    Abstract: A variable geometry inlet guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning inlet flow to a turbine or compressor and an internal spar spaced from the airfoil shell by an air gap. A number of actuation mechanisms grounded to the spar and connected to the inner surface of the aerodynamic shell adjust the shape of the shell in response to varying operating conditions of the engine, imbalanced aerodynamic loading of the shell or vibration or other transient loads on the shell.
    Type: Application
    Filed: September 1, 2006
    Publication date: March 6, 2008
    Applicant: United Technologies
    Inventors: Nagendra Somanath, Keshava B. Kumar
  • Publication number: 20080022692
    Abstract: An engine casing for a mid-turbine frame having a plurality of radially extending struts includes a ring structure and at least one mount. The ring structure has an interior surface, an exterior surface, and a plurality of equally spaced dimples along the exterior surface and protruding from the interior surface. The ring structure is connected to each of the plurality of struts at the interior surface at the dimples. The mount is positioned within each of the dimples and transfers load to the engine casing.
    Type: Application
    Filed: July 27, 2006
    Publication date: January 31, 2008
    Applicant: United Technologies Corporation
    Inventors: Somanath Nagendra, Keshava B. Kumar, William A. Sowa
  • Patent number: 7153111
    Abstract: A screw machine (10) has a rotor housing (12) defining overlapping bores (12-1, 12-2). Female rotor (14) is located in bore (12-1) and male rotor (16) is located in bore (12-2). A wear resistant coating is deposited on the tips (14-1, 16-1) of the rotors. A conformable coating is deposited on the valleys (14-2, 16-2) of the rotors. A conformable coating is depsoited on the surface of the bores coacting with the rotors.
    Type: Grant
    Filed: December 2, 2002
    Date of Patent: December 26, 2006
    Assignee: Carrier Corporation
    Inventors: James W. Bush, Clark V. Cooper, Ronald T. Drost, Hong Du, Harry E. Eaton, Hussein E. Khalifa, Keshava B. Kumar, Reng Rong Lin, Philip H. McCluskey, Paula R. DeBlois, legal representative, Raymond DeBlois, deceased
  • Patent number: 6988877
    Abstract: A screw machine (10) has a rotor housing (12) defining overlapping bores (12-1, 12-2). Female rotor (14) is located in bore (12-1) and male rotor (16) is located in bore (12-2). A wear resistant coating is deposited on the tips (14-1, 16-1) of the rotors. A conformable coating is deposited on the valleys (14-2, 16-2) of the rotors. A conformable coating is deposited on the surface of the bores coacting with the rotors.
    Type: Grant
    Filed: December 2, 2002
    Date of Patent: January 24, 2006
    Assignee: Carrier Corporation
    Inventors: James W. Bush, Clark V. Cooper, Ronald T. Drost, Hong Du, Harry E. Eaton, Hussein E. Khalifa, Keshava B. Kumar, Reng Rong Lin, Philip H. McCluskey, Paula R. DeBlois, legal representative, Raymond DeBlois, deceased
  • Patent number: 6986652
    Abstract: A screw machine (10) has a rotor housing (12) defining overlapping bores (12-1, 12-2). Female rotor (14) is located in bore (12-1) and male rotor (16) is located in bore (12-2). A wear resistant coating is deposited on the tips (14-1, 16-1) of the rotors. A conformable coating is deposited on the valleys (14-2, 16-2) of the rotors. A conformable coating is depsoited on the surface of the bores coacting with the rotors.
    Type: Grant
    Filed: December 2, 2002
    Date of Patent: January 17, 2006
    Assignee: Carrier Corporation
    Inventors: James W. Bush, Clark V. Cooper, Ronald T. Drost, Hong Du, Harry E. Eaton, Hussein E. Khalifa, Keshava B. Kumar, Reng Rong Lin, Philip H. McCluskey, Paula R. DeBlois, legal representative, Raymond DeBlois, deceased
  • Patent number: 6893240
    Abstract: A screw machine (10) has a rotor housing (12) defining overlapping bores (12-1, 12-2). Female rotor (14) is located in bore (12-1) and male rotor (16) is located in bore (12-2). A wear resistant coating is deposited on the tips (14-1, 16-1) of the rotors. A conformable coating is deposited on the valleys (14-2, 16-2) of the rotors. A conformable coating is depsoited on the surface of the bores coacting with the rotors.
    Type: Grant
    Filed: December 2, 2002
    Date of Patent: May 17, 2005
    Assignee: Carrier Corporation
    Inventors: James W. Bush, Clark V. Cooper, Ronald T. Drost, Hong Du, Harry E. Eaton, Hussein E. Khalifa, Keshava B. Kumar, Reng Rong Lin, Philip H. McCluskey, Paula R. DeBlois, Raymond DeBlois
  • Publication number: 20040033152
    Abstract: A screw machine (10) has a rotor housing (12) defining overlapping bores (12-1, 12-2). Female rotor (14) is located in bore (12-1) and male rotor (16) is located in bore (12-2). A wear resistant coating is deposited on the tips (14-1, 16-1) of the rotors. A conformable coating is deposited on the valleys (14-2, 16-2) of the rotors. A conformable coating is depsoited on the surface of the bores coacting with the rotors.
    Type: Application
    Filed: December 2, 2002
    Publication date: February 19, 2004
    Inventors: James W. Bush, Clark V. Cooper, Ronald T. Drost, Hong Du, Harry E. Eaton, Hussein E. Khalifa, Keshava B. Kumar, Reng Rong Lin, Philip H. McCluskey, Raymond DeBlois, Paula R. DeBlois
  • Publication number: 20030086807
    Abstract: A screw machine (10) has a rotor housing (12) defining overlapping bores (12-1, 12-2). Female rotor (14) is located in bore (12-1) and male rotor (16) is located in bore (12-2). A wear resistant coating is deposited on the tips (14-1, 16-1) of the rotors. A conformable coating is deposited on the valleys (14-2, 16-2) of the rotors. A conformable coating is depsoited on the surface of the bores coacting with the rotors.
    Type: Application
    Filed: December 2, 2002
    Publication date: May 8, 2003
    Inventors: James W. Bush, Clark V. Cooper, Ronald T. Drost, Hong Du, Harry E. Eaton, Hussein E. Khalifa, Keshava B. Kumar, Reng Rong Lin, Philip H. McCluskey, Raymond DeBlois, Paula R. DeBlois
  • Publication number: 20030086806
    Abstract: A screw machine (10) has a rotor housing (12) defining overlapping bores (12-1, 12-2). Female rotor (14) is located in bore (12-1) and male rotor (16) is located in bore (12-2). A wear resistant coating is deposited on the tips (14-1, 16-1) of the rotors. A conformable coating is deposited on the valleys (14-2, 16-2) of the rotors. A conformable coating is depsoited on the surface of the bores coacting with the rotors.
    Type: Application
    Filed: December 2, 2002
    Publication date: May 8, 2003
    Inventors: James W. Bush, Clark V. Cooper, Ronald T. Drost, Hong Du, Harry E. Eaton, Hussein E. Khalifa, Keshava B. Kumar, Reng Rong Lin, Philip H. McCluskey, Raymond DeBlois, Paula R. DeBlois