Patents by Inventor Peeyush Pankaj

Peeyush Pankaj 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: 20220178310
    Abstract: An epicyclic gearbox is configured to transfer rotational motion between a first rotating component and a second rotating component of the gas turbine engine. The gearbox includes a centrally located sun gear, two or more planet gears circumscribing the sun gear, and a ring gear circumscribing the plurality of planet gears. The gearbox is configured such that the sun gear is drivingly coupled to the first rotating component, such that rotation of the sun gear causes rotation of each planet gear, and such that the ring gear rotates relative to the plurality of planet gears. The gearbox includes one or more shape memory alloy dampers provided in association with the sun gear, the ring gear, and/or the plurality of planet gears. The shape memory alloy damper(s) is configured in order to reduce vibrations transferred through the epicyclic gearbox to the frame, the first rotating component, and/or the second rotating component.
    Type: Application
    Filed: September 13, 2021
    Publication date: June 9, 2022
    Inventors: Peeyush Pankaj, Narayanan Payyoor, Shashank Suresh Puranik, Arvind Kumar Rao, Praveen Sharma, Chirayu Pradip Inamdar, Vidyashankar Ramasastry Buravalla, Sankarapandian Palaniappan, Sampath Karthikeyan
  • Publication number: 20220163428
    Abstract: Systems, methods, and a gas turbine engine that includes features for condition monitoring of a damper thereof are provided. In one aspect, a gas turbine engine includes a rotary component, a bearing operatively coupled with the rotary component, and a damper associated with the bearing. The gas turbine engine also includes sensors and a controller. The controller receives data that includes sensed and/or calculated parameter values. The controller generates a damper severity index based on the parameter values. The damper severity index indicates a health state of the damper. The controller determines whether the damper severity index exceeds a threshold. When the damper severity index exceeds the threshold, a notification indicating the health state of the damper is generated. A computing system can determine a fault type and a remaining useful life of the damper and can update controller logic based on field data received from engines in a fleet.
    Type: Application
    Filed: November 23, 2020
    Publication date: May 26, 2022
    Inventors: Kanahayya Dudhale, Peeyush Pankaj, Praveen Sharma
  • Publication number: 20220145798
    Abstract: An interdigitated turbine assembly for a gas turbine engine, the interdigitated turbine assembly including a first turbine rotor assembly interdigitated with a second turbine rotor assembly. A first static frame is positioned forward of the first turbine rotor assembly and the second turbine rotor assembly. The first turbine rotor assembly is operably coupled to an inner rotatable component of a gear assembly. The second turbine rotor assembly is operably coupled to an outer rotatable component of the gear assembly. The static structure is connected to the first static frame. A driveshaft is operably coupled to the outer rotatable component. A first bearing assembly is operably coupled to the driveshaft and the first static frame. A second bearing assembly is operably coupled to the first static frame and first turbine rotor assembly. A third bearing assembly is operably coupled to the first turbine rotor assembly and the second turbine rotor assembly.
    Type: Application
    Filed: November 12, 2020
    Publication date: May 12, 2022
    Inventors: Narayanan Payyoor, Peeyush Pankaj, Richard Schmidt
  • Publication number: 20220128009
    Abstract: A turbomachine engine and gear assembly is provided. The engine includes a first power input component rotatable along a first direction relative to the engine centerline axis, a second power input component rotatable along a second direction relative to the engine centerline axis, a power output component rotatable relative to the engine centerline axis, a static component fixed relative to a circumferential direction relative to a gear assembly centerline axis, and a gear assembly. The gear assembly includes a first rotatable gear operably coupled to the first power input component at a first interface. The first rotatable gear is operably coupled to the static component at a static component interface. The static component interface is configured to react against the first rotatable gear to rotate the first rotatable gear relative to the gear assembly centerline axis. The power output component is operably coupled to the first rotatable gear.
    Type: Application
    Filed: September 1, 2021
    Publication date: April 28, 2022
    Inventors: Peeyush Pankaj, Narayanan Payyoor, Shashank Suresh Puranik
  • Publication number: 20220120291
    Abstract: Damping devices, turbomachines, and methods of damping vibration are provided. For example, a damping device for damping vibration of a shaft rotatable about an axis of rotation is provided. The damping device defines radial and axial directions. The damping device comprises a bearing, a housing, and a damper element. The housing and damper element define a cavity therebetween for receipt of a damping fluid. The cavity has a length along the axial direction that is curved away from the axis of rotation. As another example, a turbomachine comprising a shaft rotatable about an axis of rotation includes a damping device positioned annularly about the shaft. The damping device comprises a housing and a damper element defining a cavity therebetween for receipt of a damping fluid that has a curved shape. The cavity is curved in a plane extending along the radial and axial directions and including the axis of rotation.
    Type: Application
    Filed: October 19, 2020
    Publication date: April 21, 2022
    Inventors: Narayanan Payyoor, Peeyush Pankaj
  • Publication number: 20220119123
    Abstract: A propulsion system for an aircraft including a core engine connected to a forward frame and a turbine frame assembly, and an aft frame assembly is connected by a turbine casing to the core engine aft of the turbine frame assembly. A core cowl surrounds the core engine, wherein the core cowl is connected to the forward frame. A plurality of cowl mount links selectively loads the core cowl to the aft frame assembly and the turbine frame assembly, wherein the plurality of cowl mount links is each loaded by deflection of the core engine.
    Type: Application
    Filed: September 1, 2021
    Publication date: April 21, 2022
    Inventors: Peeyush Pankaj, Narayanan Payyoor, Richard Schmidt
  • Patent number: 11280219
    Abstract: A rotor support system for a gas turbine engine includes a rotatable drum rotor and a non-rotatable support casing. The rotor support system includes a bearing assembly configured for positioning between the rotatable drum rotor and the non-rotatable support casing. The bearing assembly includes, at least, a stationary support frame and a rotatable race. Further, the rotatable race is configured to engage the rotatable drum rotor at separate and discrete locations that are circumferentially spaced apart around the rotatable drum rotor.
    Type: Grant
    Filed: November 27, 2019
    Date of Patent: March 22, 2022
    Assignee: General Electric Company
    Inventors: Shashank Suresh Puranik, Bhaskar Nanda Mondal, Richard Schmidt, Peeyush Pankaj, Narayanan Payyoor
  • Patent number: 11274557
    Abstract: A gas turbine engine includes a rotatable drum rotor having a plurality of blades secured thereto. The blades extend radially inward of the rotatable drum rotor. The gas turbine engine also includes a support frame mounted radially outward of the rotating drum rotor and a rotor support system having a bearing assembly positioned between the rotatable drum rotor and the support frame. The bearing assembly includes, at least, a stationary component and at least one rotatable component. Further, the gas turbine engine includes a damper assembly for securing between the support frame and the rotatable drum rotor. Moreover, the damper assembly includes at least one damper secured between the support frame and the stationary component of the bearing assembly or to a surface of the rotatable drum rotor. As such, the damper(s) is configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.
    Type: Grant
    Filed: November 27, 2019
    Date of Patent: March 15, 2022
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Narayanan Payyoor, Shashank Suresh Puranik
  • Publication number: 20210388739
    Abstract: A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin, wherein one or more of the plurality of core layers of reinforcing fibers comprises a shear thickening fluid. The core layer may include at least one fabric sheet comprising the reinforcing fibers.
    Type: Application
    Filed: June 16, 2020
    Publication date: December 16, 2021
    Inventors: Arvind Namadevan, Arnab Sen, Wendy Wenling Lin, Shivam Mittal, Peeyush Pankaj, Shashank Suresh Puranik, Narayanan Payyoor, Praveen Sharma
  • Patent number: 11098592
    Abstract: A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: August 24, 2021
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal
  • Publication number: 20210156256
    Abstract: A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.
    Type: Application
    Filed: November 27, 2019
    Publication date: May 27, 2021
    Inventors: Peeyush Pankaj, Narayanan Payyoor, Richard Schmidt, Bugra Han Ertas
  • Publication number: 20210156257
    Abstract: A gas turbine engine includes a rotatable drum rotor having a plurality of blades secured thereto. The blades extend radially inward of the rotatable drum rotor. The gas turbine engine also includes a support frame mounted radially outward of the rotating drum rotor and a rotor support system having a bearing assembly positioned between the rotatable drum rotor and the support frame. The bearing assembly includes, at least, a stationary component and at least one rotatable component. Further, the gas turbine engine includes a damper assembly for securing between the support frame and the rotatable drum rotor. Moreover, the damper assembly includes at least one damper secured between the support frame and the stationary component of the bearing assembly or to a surface of the rotatable drum rotor. As such, the damper(s) is configured to provide damping to the rotatable drum rotor during operation of the gas turbine engine.
    Type: Application
    Filed: November 27, 2019
    Publication date: May 27, 2021
    Inventors: Peeyush Pankaj, Narayanan Payyoor, Shashank Suresh Puranik
  • Publication number: 20210156279
    Abstract: A rotor support system for a gas turbine engine includes a rotatable drum rotor and a non-rotatable support casing. The rotor support system includes a bearing assembly configured for positioning between the rotatable drum rotor and the non-rotatable support casing. The bearing assembly includes, at least, a stationary support frame and a rotatable race. Further, the rotatable race is configured to engage the rotatable drum rotor at separate and discrete locations that are circumferentially spaced apart around the rotatable drum rotor.
    Type: Application
    Filed: November 27, 2019
    Publication date: May 27, 2021
    Inventors: Shashank Suresh Puranik, Bhaskar Nanda Mondal, Richard Schmidt, Peeyush Pankaj, Narayanan Payyoor
  • Publication number: 20210148246
    Abstract: Systems and techniques that facilitate predictive core rub diagnostics are provided. A sensor component can collect real-time operation parameters of a gas turbine engine. An analysis component can statistically combine first values, second values, and third values to yield a rub indicator for the engine. The first values can be based on a first comparison of fundamental mode placements of the engine, derived from the real-time operation parameters, and baseline fundamental mode placements. The second values can be based on a second comparison of a vibration spectrum of the engine, derived from the real-time operation parameters, and a baseline vibration spectrum. The third values can be based on a third comparison of the real-time operation parameters of the engine and baseline operation parameters. A classification component can generate a rub classification report indicating presence of rubbing in the engine, based on the rub indicator.
    Type: Application
    Filed: November 14, 2019
    Publication date: May 20, 2021
    Inventors: Praveen Thirumalasetty, Peeyush Pankaj, Rajesh Kumar Undipalli, Manoj Nayani
  • Patent number: 10914194
    Abstract: A turbomachine includes a spool and a turbine section including a turbine rear frame, a turbine, and a support member. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The support member extends between the first plurality of turbine rotor blades and the spool and couples the first plurality of turbine rotor blades to the spool. The turbomachine also includes a bearing assembly including a bearing, the bearing rotatably supporting the support member and supported by the turbine rear frame, the bearing spaced apart from the spool along the radial direction.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: February 9, 2021
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal
  • Patent number: 10823000
    Abstract: A turbomachine includes a spool and a turbine section. The turbine section includes a turbine center frame and a turbine, with the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades. The first plurality of turbine rotor blades and second plurality of turbine rotor blades are alternatingly spaced along the axial direction. The turbomachine also includes a gearbox aligned with, or positioned aft of, a midpoint of the turbine. The gearbox includes a first gear coupled to the first plurality of rotor blades, a second gear coupled to the second plurality of rotor blades, and a third gear coupled to the turbine center frame. The turbomachine also includes a support member, the first plurality of turbine rotor blades coupled to the spool through the support member, the support member extending aft of the gearbox.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt
  • Patent number: 10823001
    Abstract: A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal, Ramana Reddy Kollam
  • Patent number: 10781717
    Abstract: A turbomachine includes a turbine frame and a turbine, the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a first support member assembly including a first support member supporting the first plurality of turbine rotor blades; a second support member assembly including a second support member supporting the second plurality of turbine rotor blades; a frame support member assembly including a frame support member coupled to and extending from the turbine frame; and a bearing assembly including a first bearing and a second bearing. The first bearing is positioned between the first support member and the second support member, and the second bearing is positioned between the frame support member and one of the first support member or the second support member.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: September 22, 2020
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt
  • Patent number: 10738617
    Abstract: A turbomachine includes a turbine section including a turbine center frame and a turbine, the turbine including a plurality of low-speed turbine rotor blades and a plurality of high-speed turbine rotor blades alternatingly spaced along the axial direction. The plurality of low-speed turbine rotor blades each extend between a radial inner end and a radial outer end. At least two of the plurality of low-speed turbine rotor blades are spaced from one another along the axial direction and coupled to one another at the radial outer ends. The turbomachine also includes a gearbox aligned with, or positioned forward of, a midpoint of the turbine. The gearbox includes a first gear coupled to the plurality of low-speed turbine rotor blades, a second gear coupled to the plurality of high-speed turbine rotor blades, and a third gear coupled to the turbine center frame.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt
  • Patent number: 10508546
    Abstract: A turbomachine includes a turbine section including a turbine, the turbine having a plurality of turbine rotor blades spaced along the axial direction, each turbine rotor blade extending generally along the radial direction between a radial inner end and a radial outer end. The plurality of turbine rotor blades includes a first turbine rotor blade; and a second turbine rotor blade spaced from the first turbine rotor blade along the axial direction, the radial outer end of the first turbine rotor blade coupled to the radial outer end of the second turbine rotor blade. The plurality of turbine rotor blades additionally includes a third turbine rotor blade spaced from the second turbine rotor blade along the axial direction, the radial inner end of the second turbine rotor blade coupled to the radial inner end of the third turbine rotor blade.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: December 17, 2019
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt