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).

  • Patent number: 10060291
    Abstract: A turbine section of a gas turbine engine includes a first turbine supported for rotation about an axis, a second turbine spaced axially aft of the for first turbine section for rotation about the axis, and a mid-turbine frame disposed between the first turbine and the second turbine defining a passage between the first turbine and the second turbine. A first case surrounds the first turbine and a second case surrounding the second turbine and attached to the first case. The mid-turbine frame is disposed between the first turbine section and the second turbine section and includes at least one support structure extending through an interface between the first turbine case and the second turbine case.
    Type: Grant
    Filed: February 18, 2014
    Date of Patent: August 28, 2018
    Assignee: United Technologies Corporation
    Inventor: Keshava B. Kumar
  • Publication number: 20160017754
    Abstract: A turbine section of a gas turbine engine includes a first turbine supported for rotation about an axis, a second turbine spaced axially aft of the for first turbine section for rotation about the axis, and a mid-turbine frame disposed between the first turbine and the second turbine defining a passage between the first turbine and the second turbine. A first case surrounds the first turbine and a second case surrounding the second turbine and attached to the first case. The mid-turbine frame is disposed between the first turbine section and the second turbine section and includes at least one support structure extending through an interface between the first turbine case and the second turbine case.
    Type: Application
    Filed: February 18, 2014
    Publication date: January 21, 2016
    Inventor: Keshava B. Kumar
  • Patent number: 8707710
    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: Grant
    Filed: September 18, 2009
    Date of Patent: April 29, 2014
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar
  • Patent number: 8568083
    Abstract: A gas turbine engine is provided that includes a low pressure spool, a high pressure spool, a stationary support frame, and at least one support arch. The low pressure spool extends between a low pressure compressor and a low pressure turbine. The high pressure spool extends between a high pressure compressor and a high pressure turbine. The spools are rotatable about a center axis of the engine. The support arch has a stationary support mount disposed between a low spool mount and a high spool mount. The support arch is disposed relative to the spools and the stationary support frame so that a load from each spool caused by the rotation of that spool can be transferred to the stationary support frame through the support arch. The support arch can freely rotate about the center axis of the engine relative to the spools and the stationary structural frame.
    Type: Grant
    Filed: September 4, 2009
    Date of Patent: October 29, 2013
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar, William A. Sowa
  • Patent number: 8388306
    Abstract: A method for varying the geometry of a mid-turbine frame includes detecting a strain in a mid-turbine frame with a piezoelectric material; applying a deformation voltage to the piezoelectric material as a function of the detected strain; deforming the piezoelectric material to actuate an actuation plate; and repositioning an engine casing through the actuation of the actuation plate.
    Type: Grant
    Filed: January 12, 2012
    Date of Patent: March 5, 2013
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar, Christopher M. Dye
  • Patent number: 8181467
    Abstract: A single point load structure transfers a first load from a first bearing cone and a second load from a second bearing cone of a gas turbine engine to a plurality of struts. The single point load structure includes a stem, a branch connected to the stem and a torque box connected to the plurality of struts for absorbing the first and second loads from the stem and the branch. The stem has a concave surface that opens in a radially outward direction with respect to a rotational axis of the gas turbine engine.
    Type: Grant
    Filed: June 28, 2010
    Date of Patent: May 22, 2012
    Assignee: United Technologies Corporation
    Inventors: Keshava B. Kumar, Nagendra Somanath, William A. Sowa
  • Patent number: 8181466
    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 single point load shell structure and a plurality of struts. The single point load shell structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load shell structure to the mount.
    Type: Grant
    Filed: June 28, 2010
    Date of Patent: May 22, 2012
    Assignee: United Technologies Corporation
    Inventors: Keshava B. Kumar, Nagendra Somanath, William A. Sowa
  • Publication number: 20120107087
    Abstract: A method for varying the geometry of a mid-turbine frame includes detecting a strain in a mid-turbine frame with a piezoelectric material; applying a deformation voltage to the piezoelectric material as a function of the detected strain; deforming the piezoelectric material to actuate an actuation plate; and repositioning an engine casing through the actuation of the actuation plate.
    Type: Application
    Filed: January 12, 2012
    Publication date: May 3, 2012
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nagendra Somanath, Keshava B. Kumar, Christopher M. Dye
  • Patent number: 8113768
    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: Grant
    Filed: July 23, 2008
    Date of Patent: February 14, 2012
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar, Christopher M. Dye
  • Patent number: 8075259
    Abstract: An airfoil with turning flow comprises a first surface, a second surface, a leading edge and a trailing edge. The first and second surfaces extend from the leading edge to a trailing edge. A chord extends from a midpoint of the leading edge to a midpoint of the trailing edge, defining a duct angle of at least fifteen degrees with respect to a turbine axis. An axial length of the chord defines an aspect ratio of at most one with respect to an average radial span of the leading and trailing edges. In a region of the trailing edge, an axial angle is at most four degrees and a circumferential angle is at most ten degrees, where the circumferential angle is defined in a direction opposite the turning flow.
    Type: Grant
    Filed: February 13, 2009
    Date of Patent: December 13, 2011
    Assignee: United Technologies Corporation
    Inventors: Thomas J. Praisner, Eunice Allen-Bradley, Shankar S. Magge, Keshava B. Kumar
  • Patent number: 8001791
    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: Grant
    Filed: November 13, 2007
    Date of Patent: August 23, 2011
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Christopher M. Dye, Keshava B. Kumar
  • Publication number: 20110056213
    Abstract: A gas turbine engine is provided that includes a low pressure spool, a high pressure spool, a stationary support frame, and at least one support arch. The low pressure spool extends between a low pressure compressor and a low pressure turbine. The high pressure spool extends between a high pressure compressor and a high pressure turbine. The spools are rotatable about a center axis of the engine. The support arch has a stationary support mount disposed between a low spool mount and a high spool mount. The support arch is disposed relative to the spools and the stationary support frame so that a load from each spool caused by the rotation of that spool can be transferred to the stationary support frame through the support arch. The support arch can freely rotate about the center axis of the engine relative to the spools and the stationary structural frame.
    Type: Application
    Filed: September 4, 2009
    Publication date: March 10, 2011
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nagendra Somanath, Keshava B. Kumar, William A. Sowa
  • Publication number: 20110030386
    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 single point load shell structure and a plurality of struts. The single point load shell structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load shell structure to the mount.
    Type: Application
    Filed: June 28, 2010
    Publication date: February 10, 2011
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Keshava B. Kumar, Somanath Nagendra, William A. Sowa
  • Publication number: 20110030387
    Abstract: A single point load structure transfers a first load from a first bearing cone and a second load from a second bearing cone of a gas turbine engine to a plurality of struts. The single point load structure includes a stem, a branch connected to the stem and a torque box connected to the plurality of struts for absorbing the first and second loads from the stem and the branch. The stem has a concave surface that opens in a radially outward direction with respect to a rotational axis of the gas turbine engine.
    Type: Application
    Filed: June 28, 2010
    Publication date: February 10, 2011
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Keshava B. Kumar, Nagendra Somanath, William A. Sowa
  • Patent number: 7815417
    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: Grant
    Filed: September 1, 2006
    Date of Patent: October 19, 2010
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar
  • Patent number: 7797946
    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: Grant
    Filed: December 6, 2006
    Date of Patent: September 21, 2010
    Assignee: United Technologies Corporation
    Inventors: Keshava B. Kumar, Nagendra Somanath, William A. Sowa
  • Publication number: 20100209238
    Abstract: An airfoil with turning flow comprises a first surface, a second surface, a leading edge and a trailing edge. The first and second surfaces extend from the leading edge to a trailing edge. A chord extends from a midpoint of the leading edge to a midpoint of the trailing edge, defining a duct angle of at least fifteen degrees with respect to a turbine axis. An axial length of the chord defines an aspect ratio of at most one with respect to an average radial span of the leading and trailing edges. In a region of the trailing edge, an axial angle is at most four degrees and a circumferential angle is at most ten degrees, where the circumferential angle is defined in a direction opposite the turning flow.
    Type: Application
    Filed: February 13, 2009
    Publication date: August 19, 2010
    Applicant: United Technologies Corporation
    Inventors: Thomas J. Praisner, Eunice Allen-Bradley, Shankar S. Magge, Keshava B. Kumar
  • Patent number: 7775049
    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 single point load structure and a plurality of struts. The single point load structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load structure to the mount.
    Type: Grant
    Filed: April 4, 2006
    Date of Patent: August 17, 2010
    Assignee: United Technologies Corporation
    Inventors: Keshava B. Kumar, Nagendra Somanath, William A. Sowa
  • Patent number: 7762087
    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: Grant
    Filed: December 6, 2006
    Date of Patent: July 27, 2010
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar, William A. Sowa, Christopher Dye
  • Patent number: 7677047
    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 plurality of inverted panels and a plurality of struts. The inverted panels convert the first and second loads to a shear flow. The struts are connected to the inverted panels and transfer the shear flow to the mount.
    Type: Grant
    Filed: March 29, 2006
    Date of Patent: March 16, 2010
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar, Joseph James Sedor