Patents by Inventor Kishore Ramakrishnan

Kishore Ramakrishnan 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: 20250257699
    Abstract: A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.
    Type: Application
    Filed: April 3, 2025
    Publication date: August 14, 2025
    Inventors: Trevor Howard Wood, Thomas Malkus, Kishore Ramakrishnan
  • Patent number: 12378887
    Abstract: An airfoil assembly for a gas turbine engine includes a first blade having a first leading edge and a first trailing edge, and a second blade circumferentially spaced from the first blade where the second blade has a second leading edge and a second trailing edge. The first blade includes a feature formed on the first leading edge where the first blade includes a chord extending from the first leading edge to the first trailing edge. The chord is located radially where a projection of a line normal to an intersection of the chord with the first trailing edge intersects the second leading edge. At least a portion of the feature is radially located at or inboard of the chord.
    Type: Grant
    Filed: November 28, 2022
    Date of Patent: August 5, 2025
    Assignee: General Electric Company
    Inventors: Kishore Ramakrishnan, Valeria Andreoli, Trevor Howard Wood
  • Publication number: 20250243825
    Abstract: A propulsor is provided having a power source; a fan section coupled to the power source and configured to provide thrust opposite a downstream direction; and a cowl assembly at least partially enclosing the power source and the fan section, the cowl assembly including: a forward cowl component; a first aft cowl component disposed in the downstream direction relative to the forward cowl component and movable to vary a first aft cowl displacement from the forward cowl component in the downstream direction; and a second aft cowl component disposed in the downstream direction relative to the first aft cowl component and movable to vary a second aft cowl intermediate displacement from the first aft cowl component.
    Type: Application
    Filed: March 5, 2025
    Publication date: July 31, 2025
    Inventors: Thomas Malkus, Trevor Howard Wood, Kishore Ramakrishnan
  • Publication number: 20250223909
    Abstract: A turbofan engine defining a circumferential direction is provided. The turbofan engine includes a turbomachine; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes each defining a span, the spans of the plurality of outlet guide vanes being nonuniform along the circumferential direction.
    Type: Application
    Filed: March 25, 2025
    Publication date: July 10, 2025
    Inventors: Kishore Ramakrishnan, Ravish Karve, Sara Elizabeth Carle, Trevor Howard Wood
  • Publication number: 20250206454
    Abstract: An aircraft engine includes a low pressure spool, a high pressure spool, and an alternative power source. The alternative power source is configured to add power to the high pressure spool. A controller is configured to determine a noise sensitive condition; and control, in response to determining the noise sensitive condition, the alternative power source to add power to the high pressure spool.
    Type: Application
    Filed: March 7, 2025
    Publication date: June 26, 2025
    Inventors: Kishore Ramakrishnan, Trevor Howard Wood, Harry Kirk Mathews, JR., Eric Richard Westervelt, Honggang Wang, Timothy Richard DePuy
  • Publication number: 20250198300
    Abstract: An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
    Type: Application
    Filed: March 5, 2025
    Publication date: June 19, 2025
    Inventors: Trevor Howard Wood, Kishore Ramakrishnan
  • Patent number: 12312969
    Abstract: Airfoil include a body extending along a spanwise direction between a root end and a tip end, the body comprising a plurality of acoustic cavities each having an inlet on the airfoil; and at least one cooling channel having an inlet section an outlet section and a middle section within the airfoil extending between the inlet section and the outlet section; and at least one porous face sheet positioned on at least one inlet of the plurality of acoustic cavities.
    Type: Grant
    Filed: January 17, 2023
    Date of Patent: May 27, 2025
    Assignee: General Electric Company
    Inventors: Trevor Howard Wood, Kishore Ramakrishnan, William Dwight Gerstler, Changjie Sun, Lana Maria Osusky
  • Publication number: 20250154872
    Abstract: An unducted airfoil assembly includes an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges. The airfoil defines a forward-most axial point and is arranged around a longitudinal axis and rotates about the longitudinal axis in a rotational direction. A tip leading edge of the airfoil is circumferentially offset in a direction opposite the rotational direction relative to a circumferential location of the forward-most axial point.
    Type: Application
    Filed: January 15, 2025
    Publication date: May 15, 2025
    Inventors: Kishore Ramakrishnan, Daniel Lawrence Tweedt
  • Patent number: 12286941
    Abstract: A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.
    Type: Grant
    Filed: April 12, 2023
    Date of Patent: April 29, 2025
    Assignee: General Electric Company
    Inventors: Trevor Howard Wood, Thomas Malkus, Kishore Ramakrishnan
  • Patent number: 12275532
    Abstract: An aircraft engine includes a low pressure spool, a high pressure spool, and an alternative power source. The alternative power source is configured to add power to the high pressure spool. A controller is configured to determine a noise sensitive condition; and control, in response to determining the noise sensitive condition, the alternative power source to add power to the high pressure spool.
    Type: Grant
    Filed: August 15, 2022
    Date of Patent: April 15, 2025
    Assignee: General Electric Company
    Inventors: Kishore Ramakrishnan, Trevor Howard Wood, Harry Kirk Mathews, Jr., Eric Richard Westervelt, Honggang Wang, Timothy Richard DePuy
  • Patent number: 12276199
    Abstract: A turbofan engine defining a circumferential direction is provided. The turbofan engine includes a turbomachine; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes each defining a span, the spans of the plurality of outlet guide vanes being nonuniform along the circumferential direction.
    Type: Grant
    Filed: December 21, 2022
    Date of Patent: April 15, 2025
    Assignee: General Electric Company
    Inventors: Kishore Ramakrishnan, Ravish Karve, Sara Elizabeth Carle, Trevor Howard Wood
  • Patent number: 12258875
    Abstract: An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
    Type: Grant
    Filed: March 27, 2024
    Date of Patent: March 25, 2025
    Assignee: General Electric Company
    Inventors: Trevor Howard Wood, Kishore Ramakrishnan
  • Patent number: 12258923
    Abstract: A propulsor is provided having a power source; a fan section coupled to the power source and configured to provide thrust opposite a downstream direction; and a cowl assembly at least partially enclosing the power source and the fan section, the cowl assembly including: a forward cowl component; a first aft cowl component disposed in the downstream direction relative to the forward cowl component and movable to vary a first aft cowl displacement from the forward cowl component in the downstream direction; and a second aft cowl component disposed in the downstream direction relative to the first aft cowl component and movable to vary a second aft cowl intermediate displacement from the first aft cowl component.
    Type: Grant
    Filed: March 13, 2023
    Date of Patent: March 25, 2025
    Assignee: General Electric Company
    Inventors: Thomas Malkus, Trevor Howard Wood, Kishore Ramakrishnan
  • Patent number: 12228053
    Abstract: A turbofan engine and an outlet guide vane structure for the turbofan engine is provided. The outlet guide vane structure includes a non-uniform plurality of outlet guide vanes utilized in a bypass duct and between a radially inward wall and a radially outward wall. The non-uniform plurality of outlet guide vanes have varying chord lengths at the base of the outlet guide vanes along the radially inward wall. The non-uniform plurality of outlet guide vanes may include structural outlet guide vanes, non-structural outlet guide vanes, and cut-out outlet guide vanes. The non-uniform plurality of outlet guide vanes include at least one outlet guide vane integrated with a pylon and/or a bifurcation of the turbofan engine. The cut-out outlet guide vane may be integrated with the pylon and/or bifurcation. The cut-out may include a leading edge and a trailing edge disposed in front of a leading edge of the pylon.
    Type: Grant
    Filed: August 9, 2023
    Date of Patent: February 18, 2025
    Assignee: General Electric Company
    Inventors: Trevor H. Wood, Kishore Ramakrishnan, Egbert Geertsema
  • Publication number: 20250052163
    Abstract: A turbofan engine and an outlet guide vane structure for the turbofan engine is provided. The outlet guide vane structure includes a non-uniform plurality of outlet guide vanes utilized in a bypass duct and between a radially inward wall and a radially outward wall. The non-uniform plurality of outlet guide vanes have varying chord lengths at the base of the outlet guide vanes along the radially inward wall. The non-uniform plurality of outlet guide vanes may include structural outlet guide vanes, non-structural outlet guide vanes, and cut-out outlet guide vanes. The non-uniform plurality of outlet guide vanes include at least one outlet guide vane integrated with a pylon and/or a bifurcation of the turbofan engine. The cut-out outlet guide vane may be integrated with the pylon and/or bifurcation. The cut-out may include a leading edge and a trailing edge disposed in front of a leading edge of the pylon.
    Type: Application
    Filed: August 9, 2023
    Publication date: February 13, 2025
    Inventors: Trevor H. Wood, Kishore Ramakrishnan, Egbert Geertsema
  • Patent number: 12215596
    Abstract: An unducted airfoil assembly includes an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges. The airfoil defines a forward-most axial point and is arranged around a longitudinal axis and rotates about the longitudinal axis in a rotational direction. A tip leading edge of the airfoil is circumferentially offset in a direction opposite the rotational direction relative to a circumferential location of the forward-most axial point.
    Type: Grant
    Filed: June 30, 2023
    Date of Patent: February 4, 2025
    Assignee: General Electric Company
    Inventors: Kishore Ramakrishnan, Daniel Lawrence Tweedt
  • Publication number: 20250012216
    Abstract: An inlet duct for a nacelle of a ducted fan engine includes an inlet portion having an inlet lip and a hardwall portion, a highlight plane defined at an upstream end of the inlet portion, and an acoustic liner downstream of the inlet portion, a hardwall-acoustic liner interface defined at an interface of the hardwall portion and the acoustic liner. The inlet portion and the acoustic liner are coupled at an inlet-acoustic liner interface extending circumferentially about an inner circumferential surface of the inlet duct. The inlet lip varies circumferentially and axially with respect to the highlight plane and the inlet centerline axis, and includes a plurality of inlet lip crests arranged along the highlight plane, and a plurality of inlet lip troughs arranged downstream of the highlight plane. The hardwall-acoustic liner interface extends circumferentially about the inner circumferential surface and is arranged axially parallel to the highlight plane.
    Type: Application
    Filed: September 20, 2024
    Publication date: January 9, 2025
    Inventors: Nikolai Pastouchenko, Kishore Ramakrishnan, Trevor H. Wood, Timothy Richard Depuy
  • Publication number: 20250003340
    Abstract: An unducted airfoil assembly includes an airfoil having spaced-apart pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced apart leading and trailing edges. The airfoil defines a forward-most axial point and is arranged around a longitudinal axis and rotates about the longitudinal axis in a rotational direction. A tip leading edge of the airfoil is circumferentially offset in a direction opposite the rotational direction relative to a circumferential location of the forward-most axial point.
    Type: Application
    Filed: June 30, 2023
    Publication date: January 2, 2025
    Inventors: Kishore Ramakrishnan, Daniel Lawrence Tweedt
  • Publication number: 20240426247
    Abstract: A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.
    Type: Application
    Filed: September 5, 2024
    Publication date: December 26, 2024
    Inventors: Trevor Howard Wood, Ramakrishna Venkata Mallina, Giridhar Jothiprasad, Kishore Ramakrishnan, Thomas Malkus
  • Publication number: 20240426316
    Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
    Type: Application
    Filed: September 6, 2024
    Publication date: December 26, 2024
    Inventors: Jixian Yao, Trevor H. Wood, Kishore Ramakrishnan, William J. Solomon, Giridhar Jothiprasad, Aaron J. King