Patents by Inventor Om P. Sharma
Om P. Sharma 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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Patent number: 12247529Abstract: An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.Type: GrantFiled: February 23, 2023Date of Patent: March 11, 2025Assignee: RTX CorporationInventors: Michael M. Joly, Zaffir A. Chaudhry, Andrzej Ernest Kuczek, Om P. Sharma, Georgi Kalitzin, Simon W. Evans
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Patent number: 11988140Abstract: A blended wing aircraft including a blended wing fuselage and at least one embedded gas turbine engine in the fuselage. The gas turbine engine includes an inlet duct formed with a generally elliptical shape that includes a first set of ellipse sections along an upper portion of the inlet duct and a second set of ellipse sections along a lower portion of the inlet duct. The inlet duct includes a vertical centerline. The first set of ellipse sections at a throat of the inlet duct is larger in area than an area of an upstream most end of the second set of ellipse sections. The area of the second set of ellipse sections increases toward a downstream end of the inlet duct. A fan section has an axis of rotation that is spaced from the vertical centerline and is disposed within an inlet duct orifice. The inlet duct is upstream of the fan section.Type: GrantFiled: January 12, 2021Date of Patent: May 21, 2024Assignee: RTX CorporationInventors: Dmytro Mykolayovych Voytovych, Om P. Sharma
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Patent number: 11904405Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.Type: GrantFiled: February 7, 2022Date of Patent: February 20, 2024Assignee: RTX CorporationInventors: Vijay Narayan Jagdale, Jesse R. Boyer, Om P. Sharma, Evan J. Butcher, Lawrence Binek, Bryan G. Dods
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Publication number: 20230193855Abstract: An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.Type: ApplicationFiled: February 23, 2023Publication date: June 22, 2023Inventors: Michael M. Joly, Zaffir A. Chaudhry, Andrzej Ernest Kuczek, Om P. Sharma, Georgi Kalitzin, Simon W. Evans
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Patent number: 11655778Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.Type: GrantFiled: August 6, 2021Date of Patent: May 23, 2023Assignee: Raytheon Technologies CorporationInventors: Michael M. Joly, Zaffir A. Chaudhry, Andrzej Ernest Kuczek, Om P. Sharma, Georgi Kalitzin, Simon W. Evans
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Publication number: 20230044195Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.Type: ApplicationFiled: August 6, 2021Publication date: February 9, 2023Inventors: Michael M. Joly, Zaffir A. Chaudhry, Andrzej Ernest Kuczek, Om P. Sharma, Georgi Kalitzin, Simon W. Evans
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Patent number: 11519289Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.Type: GrantFiled: December 6, 2019Date of Patent: December 6, 2022Assignee: Raytheon Technologies CorporationInventors: Gabriel L. Suciu, Om P. Sharma, Joseph B. Staubach, Marc J. Muldoon, Jesse M. Chandler, David Lei Ma
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Publication number: 20220154601Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.Type: ApplicationFiled: February 7, 2022Publication date: May 19, 2022Applicant: Raytheon Technologies CorporationInventors: Vijay Narayan Jagdale, Jesse R. Boyer, Om P. Sharma, Evan J. Butcher, Lawrence Binek, Bryan G. Dods
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Patent number: 11242769Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.Type: GrantFiled: December 17, 2018Date of Patent: February 8, 2022Assignee: Raytheon Technologies CorporationInventors: Vijay Narayan Jagdale, Jesse R. Boyer, Om P. Sharma, Evan Butcher, Lawrence Binek, Bryan G. Dods
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Publication number: 20210388761Abstract: A blended wing aircraft including a blended wing fuselage and at least one embedded gas turbine engine in the fuselage. The gas turbine engine includes an inlet duct formed with a generally elliptical shape that includes a first set of ellipse sections along an upper portion of the inlet duct and a second set of ellipse sections along a lower portion of the inlet duct. The inlet duct includes a vertical centerline. The first set of ellipse sections at a throat of the inlet duct is larger in area than an area of an upstream most end of the second set of ellipse sections. The area of the second set of ellipse sections increases toward a downstream end of the inlet duct. A fan section has an axis of rotation that is spaced from the vertical centerline and is disposed within an inlet duct orifice. The inlet duct is upstream of the fan section.Type: ApplicationFiled: January 12, 2021Publication date: December 16, 2021Inventors: Dmytro Mykolayovych Voytovych, Om P. Sharma
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Patent number: 11199136Abstract: An additively manufactured thermally insulating structure comprising a base layer and a fire-resistant layer adjacent to the base layer that forms an air gap therebetween. A method for assembling a miniature gas turbine engine includes additively manufacturing an additively manufactured thermally insulating structure onto a static structure of the miniature gas turbine engine.Type: GrantFiled: October 5, 2018Date of Patent: December 14, 2021Assignee: Raytheon Technologies CorporationInventors: Evan Butcher, Jesse R. Boyer, Om P. Sharma, Lawrence Binek, Bryan G. Dods, Vijay Narayan Jagdale
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Patent number: 11162416Abstract: A vehicle structure with unitary casing for an attritable gas turbine engine comprising a vehicle structure forming a unitary casing having a casing wall opposite the vehicle structure; a bypass duct formed between the casing wall and the vehicle structure, wherein the unitary casing is configured to receive a core of the attritable gas turbine engine.Type: GrantFiled: December 17, 2018Date of Patent: November 2, 2021Assignee: Raytheon Technologies CorporationInventors: Evan Butcher, Jesse R. Boyer, Om P. Sharma, Lawrence Binek, Bryan G. Dods, Vijay Narayan Jagdale
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Patent number: 11156156Abstract: A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.Type: GrantFiled: October 4, 2018Date of Patent: October 26, 2021Assignee: Raytheon Technologies CorporationInventors: Lawrence Binek, Jesse R. Boyer, Om P. Sharma, Evan Butcher, Bryan G. Dods, Vijay Narayan Jagdale
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Patent number: 11136895Abstract: A casing treatment comprising a hub having a surface, the hub being rotatable about an axis within a casing of a gas turbine engine compressor, at least one spiral groove formed in the surface extending axially relative to the axis, a stator blade fixed to the casing, wherein a tip of the stator blade is proximate to the at least one spiral groove.Type: GrantFiled: February 6, 2019Date of Patent: October 5, 2021Assignee: Raytheon Technologies CorporationInventors: Georgi Kalitzin, Gorazd Medic, Om P. Sharma, Junsok Yi, Dilip Prasad
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Publication number: 20210172333Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.Type: ApplicationFiled: December 6, 2019Publication date: June 10, 2021Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: GABRIEL L. SUCIU, Om P. Sharma, Joseph B. Staubach, Marc J. Muldoon, Jesse M. Chandler, David Lei Ma
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Patent number: 10907544Abstract: A gas turbine engine includes an inlet duct that is formed with a generally elliptical shape. The inlet duct includes a vertical centerline and a fan section that has an axis of rotation. The axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice.Type: GrantFiled: March 23, 2015Date of Patent: February 2, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Dmytro Mykolayovych Voytovych, Om P. Sharma
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Patent number: 10808545Abstract: An embodiment of a fan blade includes an interior region between a metallic pressure sidewall and a metallic suction sidewall. Each sidewall extends in span from a base to a tip, and extends in chord from a leading edge to a trailing edge. The interior region of the fan blade includes a first fully dense metallic portion and a first porous metallic portion. The first fully dense metallic portion has a volume occupying at least 10% of a total volume of the interior region, and substantially no porosity. The first porous metallic portion is integrally joined to the fully dense metallic portion, and is selected from a structured lattice, an unstructured foam, and combinations thereof.Type: GrantFiled: July 14, 2017Date of Patent: October 20, 2020Assignee: United Technologies CorporationInventors: Tahany Ibrahim El-Wardany, Matthew E. Lynch, Om P. Sharma, Catalin G. Fotache
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Publication number: 20200318549Abstract: A combustor for use in a gas turbine engine including: a radially inward heat shield panel; and a radially outward heat shield panel located radially outward of the radially inward heat shield panel, the radially inward heat shield panel and the radially outward heat shield panel being in a facing spaced relationship defining a combustion chamber therebetween, wherein at least one of the radially inward heat shield panel and the radially outward heat shield panel has a non-axisymmetric shape.Type: ApplicationFiled: April 4, 2019Publication date: October 8, 2020Inventors: Georgi Kalitzin, Gorazd Medic, Om P. Sharma, Timothy S. Snyder, Graham B. Fulton, III
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Publication number: 20200248560Abstract: A tandem fan for a boundary layer ingestion engine is disclosed. In various embodiments, the tandem fan includes a fan disk configured for rotation about a longitudinal axis; a primary fan blade extending radially from the fan disk, the primary fan blade having a primary fan blade span; and a secondary fan blade extending radially from the fan disk, the secondary fan blade having a secondary fan blade span within about ninety percent to about one-hundred percent of the primary fan blade span.Type: ApplicationFiled: February 4, 2020Publication date: August 6, 2020Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Michael M. Joly, Dilip Prasad, Om P. Sharma
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Publication number: 20200248575Abstract: A casing treatment comprising a hub having a surface, the hub being rotatable about an axis within a casing of a gas turbine engine compressor, at least one spiral groove formed in the surface extending axially relative to the axis, a stator blade fixed to the casing, wherein a tip of the stator blade is proximate to the at least one spiral groove.Type: ApplicationFiled: February 6, 2019Publication date: August 6, 2020Inventors: Georgi Kalitzin, Gorazd Medic, Om P. Sharma, Junsok Yi, Dilip Prasad