Patents by Inventor Viswanadha Gupta Sakala
Viswanadha Gupta Sakala 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).
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Publication number: 20230313688Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure corresponds to a first stiffness and the second hairpin structure corresponds to a second stiffness different than the first stiffness.Type: ApplicationFiled: June 5, 2023Publication date: October 5, 2023Inventors: Ravindra Shankar Ganiger, Viswanadha Gupta Sakala, Nicholas Joseph Kray, Ambika Shivamurthy, Kirti Arvind Petkar
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Patent number: 11753942Abstract: An airfoil for gas turbine engines is generally provided. The airfoil defines a span extending between a root and a tip, the airfoil further defines a chord at each point along the span extending between a leading edge and a trailing edge. Further, the airfoil includes at least one frangible airfoil portion, a residual airfoil portion adjacent to the at least one frangible airfoil portion, and one or more zones. The one or more zones may include a plurality of cavities, where at least one or more cavities of the plurality of cavities include inclusions, with the inclusions having one or more materials.Type: GrantFiled: April 11, 2022Date of Patent: September 12, 2023Assignee: General Electric CompanyInventors: Ravindra Shankar Ganiger, Hiranya Kumar Nath, Kirti Arvind Petkar, Viswanadha Gupta Sakala, Nicholas Joseph Kray
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Patent number: 11702940Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure and the second hairpin structure are made from different materials.Type: GrantFiled: June 20, 2022Date of Patent: July 18, 2023Assignee: General Electric CompanyInventors: Ravindra Shankar Ganiger, Viswanadha Gupta Sakala, Nicholas Joseph Kray, Ambika Shivamurthy, Kirti Arvind Petkar
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Publication number: 20220316342Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure and the second hairpin structure are made from different materials.Type: ApplicationFiled: June 20, 2022Publication date: October 6, 2022Inventors: Ravindra Shankar Ganiger, Viswanadha Gupta Sakala, Nicholas Joseph Kray, Ambika Shivamurthy, Kirti Arvind Petkar
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Patent number: 11365636Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure coupled to the first side of the exterior body and the second side of the exterior body; and a second hairpin structure coupled to the first side and the second side, the first hairpin structure in contact with the second hairpin structure.Type: GrantFiled: July 8, 2020Date of Patent: June 21, 2022Assignee: General Electric CompanyInventors: Ravindra Shankar Ganiger, Viswanadha Gupta Sakala, Nicholas Joseph Kray, Ambika Shivamurthy, Kirti Arvind Petkar
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Patent number: 11261787Abstract: An aircraft can include a turbine engine including a rotor and a stator, and also including a compressor, a combustor, and a turbine in axial flow arrangement. The aircraft can further include an anti-icing system with a magnetic field generator having a rotating portion and a non-rotating portion, as well as an array of carbon nanotubes thermally coupled to an exposed surface.Type: GrantFiled: June 22, 2018Date of Patent: March 1, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Ravindra Shankar Ganiger, Viswanadha Gupta Sakala, Nicholas Joseph Kray
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Patent number: 11242150Abstract: An aircraft can include an anti-icing system. The anti-icing system can include an array of carbon nanotubes thermally coupled to at least a first exposed surface of the aircraft. The anti-icing system can also include an array of solar cells carried by the aircraft and electrically coupled to the array of carbon nanotubes.Type: GrantFiled: June 22, 2018Date of Patent: February 8, 2022Assignee: General Electric CompanyInventors: Viswanadha Gupta Sakala, Ravindra Shankar Ganiger, Nicholas Joseph Kray
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Publication number: 20210363888Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure coupled to the first side of the exterior body and the second side of the exterior body; and a second hairpin structure coupled to the first side and the second side, the first hairpin structure in contact with the second hairpin structure.Type: ApplicationFiled: July 8, 2020Publication date: November 25, 2021Inventors: Ravindra Shankar Ganiger, Viswanadha Gupta Sakala, Nicholas Joseph Kray, Ambika Shivamurthy, Kirti Arvind Petkar
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Patent number: 11015461Abstract: Composite hollow blade and an associated method of forming the composite hollow blade are disclosed. The method includes forming a core by fabricating a grid core structure based on a plurality of design parameters, where the grid core includes a plurality of first reinforcing components disposed in a first curable matrix material. The method further includes forming an outer layer including a plurality of second reinforcing components disposed in a second curable matrix material. Further, the method includes coupling the core to the outer layer and curing the core and the outer layer to form the composite hollow blade.Type: GrantFiled: December 21, 2017Date of Patent: May 25, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Viswanadha Gupta Sakala, Douglas Duane Ward, Ming Xie
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Patent number: 10815804Abstract: A containment assembly for use in a turbine engine includes a fan case formed from a composite material. The fan case includes a forward end, an aft end, and an opening defined through the fan case between the forward and aft ends. The containment assembly further includes a structural attachment member formed from a metallic material and coupled to the fan case. The structural attachment member is positioned within the opening in the fan case and is configured to receive at least one fastener to couple a component to the structural attachment member.Type: GrantFiled: April 4, 2017Date of Patent: October 27, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Viswanadha Gupta Sakala, Mitchell Harold Boyer, Ming Xie, Douglas Duane Ward
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Patent number: 10815795Abstract: A blade for a propulsion apparatus that includes a body formed of a first material. The body includes opposed pressure and suction sides and extends in span between a root and a tip. The body extends in court between a leading edge and a trailing edge. A tension element is positioned within the body and extends between the root and the tip. The tension element includes at least one string that is configured to be under tension such that at least a portion of the blade between the root and the tip is under compression.Type: GrantFiled: December 20, 2018Date of Patent: October 27, 2020Assignee: General Electric CompanyInventors: Ravindra Shankar Ganiger, Viswanadha Gupta Sakala, Nicholas Joseph Kray
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Publication number: 20200200018Abstract: A blade for a propulsion apparatus that includes a body formed of a first material. The body includes opposed pressure and suction sides and extends in span between a root and a tip. The body extends in court between a leading edge and a trailing edge. A tension element is positioned within the body and extends between the root and the tip. The tension element includes at least one string that is configured to be under tension such that at least a portion of the blade between the root and the tip is under compression.Type: ApplicationFiled: December 20, 2018Publication date: June 25, 2020Inventors: Ravindra Shankar Ganiger, Viswanadha Gupta Sakala, Nicholas Joseph Kray
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Patent number: 10677090Abstract: An annular rotatable component for a machine includes a first element formed of a composite material, is ring-shaped, and is formed of one or more first ring segments. The first element includes a first interface surface. A second element is formed of a metallic material, is ring-shaped, and is formed of one or more second ring segments. The second element includes a second interface surface complementary to the first interface surface. The annular rotatable component also includes an interface comprising an interface material disposed between the first interface surface and the second interface surface. The interface material, the first element and the second element are co-bonded together to form a unitary structure of the annular rotatable component.Type: GrantFiled: May 10, 2017Date of Patent: June 9, 2020Assignee: General Electric CompanyInventors: Viswanadha Gupta Sakala, Wendy Wenling Lin, Raghuveer Chinta
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Patent number: 10677260Abstract: A turbine engine that includes a rotor assembly including a plurality of rotor blades, an outer case positioned radially outward from the plurality of rotor blades, and an annular ring coupled to the outer case and positioned between the plurality of rotor blades and the outer case. The annular ring is configured to restrict thermal contraction of the outer case towards the plurality of rotor blades.Type: GrantFiled: February 21, 2017Date of Patent: June 9, 2020Assignee: General Electric CompanyInventors: Veeraraju Vanapalli, Nitesh Jain, Viswanadha Gupta Sakala, Bhaskar Nanda Mondal, Nicholas Joseph Kray
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Patent number: 10583913Abstract: An aircraft spinner assembly includes collar stud joints connecting spinner to forward flange connected to fan rotor disk. Collar stud joint is operable to push out spinner when stud is un-torqued. Collar may be attached to stud disposed through spinner bolt hole in spinner and collar disposed in counterbore of spinner bolt hole. An aft stud thread on collar stud may be threaded into aft nut which may be swaged into flange bolt hole in forward flange. A washer may be in counterbore between collar and spinner and made from low friction and/or sacrificial material. A forward radial clearance may surround stud between stud and spinner. A forward nut may be threaded onto forward stud threads on forward end of the collar stud and abut spinner. External aft stud threads may be on collar studs and threaded into internal flange threads within flange bolt holes in forward flange.Type: GrantFiled: March 14, 2017Date of Patent: March 10, 2020Assignee: General Electric CompanyInventors: Abhishek Goverdhan, Ravindra Shankar Ganiger, Richa Awasthi, Viswanadha Gupta Sakala, Vidya Lokammanahalli Shivashankar
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Publication number: 20190389589Abstract: An aircraft can include an anti-icing system. The anti-icing system can include an array of carbon nanotubes thermally coupled to at least a first exposed surface of the aircraft. The anti-icing system can also include an array of solar cells carried by the aircraft and electrically coupled to the array of carbon nanotubes.Type: ApplicationFiled: June 22, 2018Publication date: December 26, 2019Inventors: Viswanadha Gupta Sakala, Ravindra Shankar Ganiger, Nicholas Joseph Kray
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Publication number: 20190390600Abstract: An aircraft can include a turbine engine including a rotor and a stator, and also including a compressor, a combustor, and a turbine in axial flow arrangement. The aircraft can further include an anti-icing system with a magnetic field generator having a rotating portion and a non-rotating portion, as well as an array of carbon nanotubes thermally coupled to an exposed surface.Type: ApplicationFiled: June 22, 2018Publication date: December 26, 2019Inventors: Ravindra Shankar Ganiger, Viswanadha Gupta Sakala, Nicholas Joseph Kray
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Patent number: 10502133Abstract: A fastener cover assembly is disclosed. The cover assembly includes a turbomachinery component having an outer surface exposed to an air flow path; at least one recess formed in the outer surface; a fastener contained in the at least one recess; and a fastener cover secured in the at least one recess, the cover having an outer surface substantially flush with the outer surface of the component to minimize air flow disruption.Type: GrantFiled: June 12, 2017Date of Patent: December 10, 2019Assignee: General Electric CompanyInventors: Richa Awasthi, Bhanu Kishore Battu, Viswanadha Gupta Sakala, Michael Jason Bishop
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Publication number: 20190195073Abstract: Composite hollow blade and an associated method of forming the composite hollow blade are disclosed. The method includes forming a core by fabricating a grid core structure based on a plurality of design parameters, where the grid core includes a plurality of first reinforcing components disposed in a first curable matrix material. The method further includes forming an outer layer including a plurality of second reinforcing components disposed in a second curable matrix material. Further, the method includes coupling the core to the outer layer and curing the core and the outer layer to form the composite hollow blade.Type: ApplicationFiled: December 21, 2017Publication date: June 27, 2019Inventors: Viswanadha Gupta Sakala, Douglas Duane Ward, Ming Xie
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Publication number: 20180355796Abstract: A fastener cover assembly is disclosed. The cover assembly includes a turbomachinery component having an outer surface exposed to an air flow path; at least one recess formed in the outer surface; a fastener contained in the at least one recess; and a fastener cover secured in the at least one recess, the cover having an outer surface substantially flush with the outer surface of the component to minimize air flow disruption.Type: ApplicationFiled: June 12, 2017Publication date: December 13, 2018Inventors: Richa Awasthi, Bhanu Kishore Battu, Viswanadha Gupta Sakala, Michael Jason Bishop