Patents by Inventor Atanu Saha
Atanu Saha 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: 20240084703Abstract: Methods for repairing a thermal barrier coating deposited on a component with localized spallation of the thermal barrier coating includes depositing a primer slurry on a thermally grown oxide of the component exposed by the localized spallation, depositing a ceramic slurry on the primer slurry, and heating the primer slurry and the ceramic slurry. The primer slurry includes a primer that includes at least one of a metal and a metal oxide. The ceramic slurry includes a ceramic material, a ceramic slurry binder material, and a ceramic slurry fluid carrier. Heating the primer slurry and the ceramic slurry forms a first chemical bond between the primer and the thermally grown oxide and a second chemical bond between the primer and the ceramic material.Type: ApplicationFiled: August 29, 2023Publication date: March 14, 2024Applicant: General Electric CompanyInventors: Atanu Saha, Hrishikesh Keshavan, Mamatha Nagesh, Ambarish J. Kulkarni, Bernard P. Bewlay
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Publication number: 20240026822Abstract: A gas turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement to define a diffuser cavity between the compressor section and the combustor section, and an aft cavity. A compressor discharge pressure duct fluidly draws air from the diffuser cavity, passes it through a heat exchanger to cool the air, and then supplies the cooled air to the aft cavity.Type: ApplicationFiled: July 20, 2022Publication date: January 25, 2024Inventors: Lakshmi Narasimharao Jagata, Prateek Jalan, Veeraraju Vanapalli, Atanu Saha, Scott Alan Schimmels
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Publication number: 20240026820Abstract: A gas turbine engine including a compressor section including a compressor and a turbine section located downstream of the compressor section. The turbine section including a high pressure turbine, a low pressure turbine, a sump positioned between the high pressure turbine and the low pressure turbine, and a rotating cross flow arrangement defining a plurality of guiding passages fluidly coupling the compressor to the sump.Type: ApplicationFiled: July 22, 2022Publication date: January 25, 2024Inventors: Vaishnav Raghuvaran, Atanu Saha, Rajesh Kumar, Scott Alan Schimmels
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Patent number: 11879411Abstract: A gas turbine engine includes a casing, a rotor assembly rotatably mounted within the casing, the rotor assembly comprising a forward rotor portion defining a forward rotor cavity and an aft rotor portion defining an aft rotor cavity, the aft rotor cavity being fluidly isolated from the forward rotor cavity, and a cooling system. The cooling system includes a forward cooling fluid supply, a forward supply line providing fluid communication between the forward cooling fluid supply and the forward rotor cavity, an aft cooling fluid supply, an aft supply line providing fluid communication between the aft cooling fluid supply and the aft rotor cavity, and a flow control system fluidly coupled to the forward supply line and the aft supply line for regulating a flow of forward cooling fluid and a flow of aft cooling fluid.Type: GrantFiled: June 13, 2022Date of Patent: January 23, 2024Assignee: General Electric CompanyInventors: Rajesh Kumar, Prateek Jalan, Kudum Shinde, Atanu Saha, Hiranya Kumar Nath, Ravindra Shankar Ganiger
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Patent number: 11859547Abstract: A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.Type: GrantFiled: May 27, 2022Date of Patent: January 2, 2024Assignee: General Electric CompanyInventors: Joseph G. Rose, Atanu Saha, Bhaskar Nanda Mondal, Craig W. Higgins, Darek Zatorski, Vaibhav Deshmukh M
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Publication number: 20230407101Abstract: A coating method is provided. The coating method includes applying, via electrophoretic deposition or slurry deposition, an overcoat composition on an outer surface of a thermal barrier coating system on a substrate. The overcoat composition includes a coating material comprising a plurality of particles having a particle size of less than 1000 nm. The method includes sintering the overcoat composition in the presence of one or more sintering aids to form an overcoat layer having a surface roughness of less than 1 micrometer.Type: ApplicationFiled: December 21, 2022Publication date: December 21, 2023Inventors: Mohandas Nayak, Sundeep Kumar, Atanu Saha, Julie Marie Kuhn
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Patent number: 11828226Abstract: In one aspect, the present disclosure is directed a gas turbine engine including a compressor, a combustor, and a turbine in a serial flow arrangement. The compressor includes a casing having an inner wall and an outer wall. The inner wall defines a passageway for airflow through the compressor. The casing defines a bleed cavity between the inner wall and the outer wall. The inner wall has an opening. The casing defining a channel between the opening and the bleed cavity to direct airflow into the bleed cavity. The channel is defined by a first wall and a second wall of the casing. The second wall being downstream of the first wall. A surface of the first wall has a pattern to reduce flow separation in the channel.Type: GrantFiled: May 27, 2022Date of Patent: November 28, 2023Assignee: General Electric CompanyInventors: Sesha Subramanian, Ravikanth Avancha, Atanu Saha
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Publication number: 20230332539Abstract: In one aspect, the present disclosure is directed a gas turbine engine including a compressor, a combustor, and a turbine in a serial flow arrangement. The compressor includes a casing having an inner wall and an outer wall. The inner wall defines a passageway for airflow through the compressor. The casing defines a bleed cavity between the inner wall and the outer wall. The inner wall has an opening. The casing defining a channel between the opening and the bleed cavity to direct airflow into the bleed cavity. The channel is defined by a first wall and a second wall of the casing. The second wall being downstream of the first wall. A surface of the first wall has a pattern to reduce flow separation in the channel.Type: ApplicationFiled: May 27, 2022Publication date: October 19, 2023Inventors: Sesha Subramanian, Ravikanth Avancha, Atanu Saha
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Publication number: 20230323835Abstract: A gas turbine engine includes a casing, a rotor assembly rotatably mounted within the casing, the rotor assembly comprising a forward rotor portion defining a forward rotor cavity and an aft rotor portion defining an aft rotor cavity, the aft rotor cavity being fluidly isolated from the forward rotor cavity, and a cooling system. The cooling system includes a forward cooling fluid supply, a forward supply line providing fluid communication between the forward cooling fluid supply and the forward rotor cavity, an aft cooling fluid supply, an aft supply line providing fluid communication between the aft cooling fluid supply and the aft rotor cavity, and a flow control system fluidly coupled to the forward supply line and the aft supply line for regulating a flow of forward cooling fluid and a flow of aft cooling fluid.Type: ApplicationFiled: June 13, 2022Publication date: October 12, 2023Inventors: Rajesh Kumar, Prateek Jalan, Kudum Shinde, Atanu Saha, Hiranya Kumar Nath, Ravindra Shankar Ganiger
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Publication number: 20230312935Abstract: Coated components, along with methods of their formation, are provided. The coating may include a component having a surface and a coating over the surface of the component. The coating may include a first plurality of coarse micrograins having an coarse median grain size of greater than 10 ?m to 20 ?m, a second plurality of medium micrograins having a medium median grain size of 4 ?m to 10 ?m, a third plurality of fine micrograins having a fine median grain size of 0.001 ?m to less than 4 ?m. Each of the coarse micrograins, medium micrograins, and fine micrograins may include, independently, a yttria-stabilized zirconia (YSZ) constituent having a chemical formula of (ZrO2)(1?x)(Y2O3)x with x is from greater than 0 to less than 1.Type: ApplicationFiled: June 16, 2022Publication date: October 5, 2023Inventors: Atanu Saha, Bernard Patrick Bewlay, Neelesh Nandkumar Sarawate
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Publication number: 20230272744Abstract: A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.Type: ApplicationFiled: May 27, 2022Publication date: August 31, 2023Inventors: Joseph G. Rose, Atanu Saha, Bhaskar Nanda Mondal, Craig W. Higgins, Darek Zatorski, Vaibhav Deshmukh M
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Patent number: 11719168Abstract: An example compressor bleed slot apparatus includes an annular compressor casing, a blade row mounted for rotation about a centerline axis inside the compressor casing, a bleed slot passing through the forward section of the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row, an array of struts interconnecting the inboard and outboard walls, and an annular supplemental flange extending radially outward from the forward section of the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot, wherein the supplemental flange includes a necked-down portion adjacent the forward section of the compressor casing, the necked-down portion positioned axially between an inlet of the bleed slot and an outlet of the bleed slot.Type: GrantFiled: March 1, 2021Date of Patent: August 8, 2023Assignee: General Electric CompanyInventors: Steven Mitchell Taylor, Vishnu Das K, Manish Singhal, Atanu Saha, Michael Anthony Thomas
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Patent number: 11655720Abstract: A sprayable thermal barrier coating powder mixture for a gas turbine engine includes: a dry composition having a low surface area ceramic powder having a median particle size distribution greater than 5 microns and less than 50 microns, and a high surface area ceramic powder having a median particle size distribution smaller than 5 microns, wherein the low surface area ceramic powder makes up at least 50% by weight of the dry composition of the sprayable thermal barrier coating powder mixture.Type: GrantFiled: May 6, 2021Date of Patent: May 23, 2023Assignee: General Electric CompanyInventors: Hrishikesh Keshavan, Atanu Saha, Margeaux Wallace, Mamatha Nagesh, Ambarish Jayant Kulkarni, Bernard Patrick Bewlay, Jr.
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Publication number: 20230101282Abstract: A corrosion resistant coating including a matrix, corrosion resistant particles dispersed throughout the matrix, and a glass-forming additive is disclosed. The glass-forming additive and one or more materials in the matrix form a glassy-phase when cured. Coated gas turbine engine components and methods for coating components are also disclosed.Type: ApplicationFiled: September 28, 2021Publication date: March 30, 2023Inventors: Mamatha Nagesh, Atanu Saha, Srinivasan Swaminathan
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Patent number: 11549382Abstract: A coated component of a gas turbine engine includes a substrate defining a surface, a thermal barrier coating deposited on the surface of the substrate, a region of the component where the thermal barrier coating has spalled from the substrate, a layer of environmental contaminant compositions formed on one or more of the thermal barrier coating or the region of the component where the thermal barrier coating has spalled from the substrate in response to an initial exposure of the component to high operating temperatures of the gas turbine engine, and a thermal barrier coating (TBC) restoration coating deposited at least on the region of the component where there thermal barrier coating has spalled from the substrate.Type: GrantFiled: November 4, 2020Date of Patent: January 10, 2023Assignee: General Electric CompanyInventors: Hrishikesh Keshavan, Ambarish Jayant Kulkarni, Margeaux Wallace, Byron Andrew Pritchard, Jr., Almed M. Elkady, Atanu Saha, Mamatha Nagesh, Bernard Patrick Bewlay
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Publication number: 20220169551Abstract: Methods for forming a sintered patch on a silicon-based substrate are disclosed. The methods include applying a patch slurry on the silicon-based substrate, drying the patch slurry on the silicon-based substrate to form a dried patch material, and sintering the dried patch material in an oxidizing atmosphere to form a sintered patch on the silicon-based substrate. The patch slurry includes a patch material containing silicates in a fluid carrier.Type: ApplicationFiled: December 1, 2020Publication date: June 2, 2022Inventors: Atanu Saha, Manepalli Satya Kishore, Nicholas Edward Antolino, Don Mark Lipkin, Mamatha Nagesh
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Publication number: 20220018293Abstract: An example compressor bleed slot apparatus includes an annular compressor casing, a blade row mounted for rotation about a centerline axis inside the compressor casing, a bleed slot passing through the forward section of the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row, an array of struts interconnecting the inboard and outboard walls, and an annular supplemental flange extending radially outward from the forward section of the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot, wherein the supplemental flange includes a necked-down portion adjacent the forward section of the compressor casing, the necked-down portion positioned axially between an inlet of the bleed slot and an outlet of the bleed slot.Type: ApplicationFiled: March 1, 2021Publication date: January 20, 2022Inventors: Steven Mitchell Taylor, Vishnu Das K, Manish Singhal, Atanu Saha, Michael Anthony Thomas
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Publication number: 20210396181Abstract: A sprayable thermal barrier coating powder mixture for a gas turbine engine includes: a dry composition having a low surface area ceramic powder having a median particle size distribution greater than 5 microns and less than 50 microns, and a high surface area ceramic powder having a median particle size distribution smaller than 5 microns, wherein the low surface area ceramic powder makes up at least 50% by weight of the dry composition of the sprayable thermal barrier coating powder mixture.Type: ApplicationFiled: May 6, 2021Publication date: December 23, 2021Inventors: Hrishikesh Keshavan, Atanu Saha, Margeaux Wallace, Mamatha Nagesh, Ambarish Jayant Kulkarni, Bernard Patrick Bewlay, JR.
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Patent number: 11193720Abstract: A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor having a compressor discharge nozzle, a combustor coupled to the compressor, a turbine coupled to the combustor and the compressor, a fluid flow passage fluidly coupling the compressor and the turbine and bypassing the combustor, and a heat absorption device disposed fluidly along the fluid flow passage at a first predefined location. The heat absorption device includes a casing having an inlet and an outlet, a flow path within the casing and extending between the inlet and the outlet, wherein the flow path directs an input bleed flow diverted from a fluid stream discharged from the compressor, and a phase change material hermetically sealed within the casing. The phase change material is separated from the flow path.Type: GrantFiled: March 24, 2020Date of Patent: December 7, 2021Assignee: General Electric CompanyInventors: Karthikeyan Sampath, Atanu Saha, Bhaskar Nanda Mondal, Sanjeev Sai Kumar Manepalli
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Patent number: 11015483Abstract: Various embodiments include a compressor casing and a method of assembly. The compressor casing comprises a first and an adjacent, second annular casing segments each comprising an annular radially-extending flange with mounting holes; at least one annular recess disposed on at least one annular side mating face of the adjacent flanges of the adjacent segments; at least one set of stress-relief holes disposed through at least one flange of the adjacent segments; and at least one annular leak-resistant plate disposed within the at least one annular recess having at least a third set of mounting holes. All sets of mounting holes are substantially aligned with each other and receive a plurality of respective fasteners, and the at least one annular plate is clamped between the adjacent segments and seals the at least one set of stress-relief holes for preventing leakage therethrough.Type: GrantFiled: March 9, 2018Date of Patent: May 25, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Vishnu Das K, Carlos Ivan Flores, Atanu Saha, Vinaykumar Shrimantrao Patil