Patents by Inventor Piotr Jerzy Kulinski
Piotr Jerzy Kulinski 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: 11859500Abstract: A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.Type: GrantFiled: December 23, 2021Date of Patent: January 2, 2024Assignees: General Electric Company, General Electric Deutschland Holding GmbH, General Electric Company Polska Sp. z o.o.Inventors: Ashish Sharma, Piotr Jerzy Kulinski, Adam Tomasz Pazinski, Tomasz Jan Bulsiewicz, Scott Alan Schimmels
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Publication number: 20230407758Abstract: A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.Type: ApplicationFiled: August 21, 2023Publication date: December 21, 2023Inventors: Ashish Sharma, Piotr Jerzy Kulinski, Adam Tomasz Pazinski, Tomasz Jan Bulsiewicz, Scott Alan Schimmels
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Patent number: 11846193Abstract: An assembly for a turbine engine can include a monolithic body with an inner band and an outer band radially spaced from the inner band, a pocket surface in one of the inner or outer bands defining a recess, and an airfoil with a first end radially extending from the other of the inner or outer bands.Type: GrantFiled: July 27, 2020Date of Patent: December 19, 2023Assignee: General Electric Company Polska Sp. z o.o.Inventors: Piotr Jerzy Kulinski, Tomasz Edward Berdowski
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Publication number: 20230340885Abstract: A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.Type: ApplicationFiled: June 28, 2023Publication date: October 26, 2023Inventors: Elzbieta Kryj-Kos, Piotr Jerzy Kulinski, Pawel Adam Lewicki, Ruolong Ma, Wendy Wenling Lin, Patrick Keene Clements
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Patent number: 11788425Abstract: A gas turbine engine including: a first turbine rotor assembly including a plurality of first turbine rotor blades extended within a gas flowpath; and a casing surrounding the first turbine rotor assembly, wherein the casing comprises an outer casing wall extended around the first turbine rotor assembly; a plurality of vanes extended from the outer casing wall and within the gas flowpath at a location aft of the first turbine rotor assembly; and a thermal control ring positioned outward along a radial direction from the outer casing wall, and wherein the thermal control ring comprises a body and a plurality of pins, and wherein the plurality of pins extend between the outer casing wall and the body.Type: GrantFiled: December 23, 2021Date of Patent: October 17, 2023Assignees: General Electric Company, General Electric Deutschland Holding GmbH, General Electric Company Polska Sp. z o.o.Inventors: Ashish Sharma, Piotr Jerzy Kulinski, Adam Tomasz Pazinski, Tomasz Jan Bulsiewicz, Scott Alan Schimmels
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Patent number: 11725524Abstract: An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.Type: GrantFiled: July 30, 2021Date of Patent: August 15, 2023Assignees: General Electric Company, General Electric Company Polska Sp. Z o.o.Inventors: Elzbieta Kryj-Kos, Piotr Jerzy Kulinski, Pawel Adam Lewicki, Ruolong Ma, Wendy Wenling Lin, Patrick Keene Clements
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Patent number: 11719115Abstract: A gas turbine engine including a first turbine rotor assembly having a plurality of first turbine rotor blades extended within a gas flowpath, and a second turbine rotor assembly positioned aft along the gas flowpath of the first turbine rotor assembly. The second turbine rotor assembly is rotatably separate from the first turbine rotor assembly. A casing surrounds the first turbine rotor assembly. The casing has a unitary, integral outer casing wall extended forward of the first turbine rotor assembly and aft of the first turbine rotor assembly. The casing includes a plurality of vanes extended from the outer casing wall and through the gas flowpath aft of the first turbine rotor assembly and forward of the second turbine rotor assembly. The casing includes a plurality of walls forming thermal control rings extended outward along the radial direction from the outer casing wall. The outer casing wall and the thermal control rings is a unitary, integral structure.Type: GrantFiled: December 23, 2021Date of Patent: August 8, 2023Assignees: GENERAL ELECTRIC COMPANY, GENERAL ELECTRIC DEUTSCHLAND HOLDING GMBH, GENERAL ELECTRIC COMPANY POLSKA SP. Z O.OInventors: Tomasz Edward Berdowski, Ashish Sharma, Raymond Floyd Martell, Piotr Jerzy Kulinski, Lukasz Maciej Janczak
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Publication number: 20230146084Abstract: A gas turbine engine including: a first turbine rotor assembly including a plurality of first turbine rotor blades extended within a gas flowpath; and a casing surrounding the first turbine rotor assembly, wherein the casing comprises an outer casing wall extended around the first turbine rotor assembly; a plurality of vanes extended from the outer casing wall and within the gas flowpath at a location aft of the first turbine rotor assembly; and a thermal control ring positioned outward along a radial direction from the outer casing wall, and wherein the thermal control ring comprises a body and a plurality of pins, and wherein the plurality of pins extend between the outer casing wall and the body.Type: ApplicationFiled: December 23, 2021Publication date: May 11, 2023Inventors: Ashish Sharma, Piotr Jerzy Kulinski, Adam Tomasz Pazinski, Tomasz Jan Bulsiewicz, Scott Alan Schimmels
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Publication number: 20230147089Abstract: A gas turbine engine including a first turbine rotor assembly having a plurality of first turbine rotor blades extended within a gas flowpath, and a second turbine rotor assembly positioned aft along the gas flowpath of the first turbine rotor assembly. The second turbine rotor assembly is rotatably separate from the first turbine rotor assembly. A casing surrounds the first turbine rotor assembly. The casing has a unitary, integral outer casing wall extended forward of the first turbine rotor assembly and aft of the first turbine rotor assembly. The casing includes a plurality of vanes extended from the outer casing wall and through the gas flowpath aft of the first turbine rotor assembly and forward of the second turbine rotor assembly. The casing includes a plurality of walls forming thermal control rings extended outward along the radial direction from the outer casing wall. The outer casing wall and the thermal control rings is a unitary, integral structure.Type: ApplicationFiled: December 23, 2021Publication date: May 11, 2023Inventors: Tomasz Edward Berdowski, Ashish Sharma, Raymond Floyd Martell, Piotr Jerzy Kulinski, Lukasz Maciej Janczak
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Publication number: 20230143283Abstract: A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.Type: ApplicationFiled: December 23, 2021Publication date: May 11, 2023Inventors: Ashish Sharma, Piotr Jerzy Kulinski, Adam Tomasz Pazinski, Tomasz Jan Bulsiewicz, Scott Alan Schimmels
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Publication number: 20220372885Abstract: A gas turbine engine is provided having a static structure including a flowpath wall. A fluid circuit is extended through the flowpath wall and includes a first inlet opening in fluid communication with a first cavity to receive a first flow of fluid through the fluid circuit. The static structure includes an ejector positioned at the fluid circuit, in which the ejector includes a second inlet opening in fluid communication with a second cavity to receive a second flow of fluid through the ejector and into the fluid circuit.Type: ApplicationFiled: July 20, 2021Publication date: November 24, 2022Inventors: Tomasz Edward Berdowski, Miroslaw Sobaniec, Maciej Czerwinski, Ashish Sharma, Piotr Jerzy Kulinski
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Publication number: 20220307380Abstract: An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.Type: ApplicationFiled: July 30, 2021Publication date: September 29, 2022Inventors: Elzbieta Kryj-Kos, Piotr Jerzy Kulinski, Pawel Adam Lewicki, Ruolong Ma, Wendy Wenling Lin, Patrick Keene Clements
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Publication number: 20210087942Abstract: An assembly for a turbine engine can include a monolithic body with an inner band and an outer band radially spaced from the inner band, a pocket surface in one of the inner or outer bands defining a recess, and an airfoil with a first end radially extending from the other of the inner or outer bands.Type: ApplicationFiled: July 27, 2020Publication date: March 25, 2021Inventors: Piotr Jerzy Kulinski, Tomasz Edward Berdowski