Patents by Inventor Tomasz Edward Berdowski
Tomasz Edward Berdowski 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: 12234742Abstract: Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example airfoil includes an outer wall having a first rib spaced apart from a second rib on a surface of the outer wall, and an inner wall surrounded by the outer wall, the inner wall having a third rib protruding from the inner wall towards the surface of the outer wall, an end of the third rib detachably coupled to a portion of the surface of the outer wall, the portion of the surface positioned between the first rib and the second rib, the third rib and at least one of the first rib or the second rib to at least partially seal a flow passage between the inner and outer walls.Type: GrantFiled: February 19, 2024Date of Patent: February 25, 2025Assignees: General Electric Company, General Electric Deutschland Holding GmbHInventors: Ashish Sharma, Tomasz Edward Berdowski, Maciej Czerwiński, Katarzyna Anna Mikolajczyk, Raymond Floyd Martell, Tomasz Jan Bulsiewicz
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Patent number: 12122529Abstract: Propulsion engines and methods of accessing components within propulsor cavities of propulsion engines are disclosed. A propulsion engine includes an outer engine housing that includes a propulsor cavity located therein. The propulsor cavity is axially located between a low-pressure compressor and a fan of the propulsion engine. An electric converter is disposed within the propulsor cavity.Type: GrantFiled: July 21, 2021Date of Patent: October 22, 2024Assignee: GENERAL ELECTRIC COMPANY POLSKA SP. Z O.OInventors: Mirosław Czarnik, Tomasz Edward Berdowski, Paweł Zdrojewski, Łukasz Maciej Janczak, Maciej Grunwald
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Publication number: 20240191638Abstract: Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example airfoil includes an outer wall having a first rib spaced apart from a second rib on a surface of the outer wall, and an inner wall surrounded by the outer wall, the inner wall having a third rib protruding from the inner wall towards the surface of the outer wall, an end of the third rib detachably coupled to a portion of the surface of the outer wall, the portion of the surface positioned between the first rib and the second rib, the third rib and at least one of the first rib or the second rib to at least partially seal a flow passage between the inner and outer walls.Type: ApplicationFiled: February 19, 2024Publication date: June 13, 2024Inventors: Ashish Sharma, Tomasz Edward Berdowski, Maciej Czerwinski, Katarzyna Anna Mikolajczyk, Raymond Floyd Martell, Tomasz Jan Bulsiewicz
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Patent number: 11905842Abstract: Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example apparatus includes an inner wall and an outer wall, the outer wall spaced apart from the inner wall in a radial direction, a space between the inner and outer walls defining a flow passage, and a body positioned between the inner and outer walls, the body traversing the inner and outer walls in an axial direction and attached to an inner surface of the outer wall and an outer surface of the inner wall, the body to detach from the inner and outer surfaces and to at least partially seal the flow passage in response to the outer wall moving relative to the inner wall.Type: GrantFiled: December 16, 2021Date of Patent: February 20, 2024Assignee: General Electric CompanyInventors: Ashish Sharma, Tomasz Edward Berdowski, Maciej Czerwiński, Katarzyna Anna Mikolajczyk, Raymond Floyd Martell, Tomasz Jan Bulsiewicz
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Patent number: 11885240Abstract: 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: GrantFiled: July 20, 2021Date of Patent: January 30, 2024Assignees: General Electric Company Polska sp.z o.o, General Electric Deutschland Holding GmbHInventors: Tomasz Edward Berdowski, Mirosław Sobaniec, Maciej Czerwiński, Ashish Sharma, Piotr Jerzy Kuliński
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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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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: 20230193784Abstract: Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example apparatus includes an inner wall and an outer wall, the outer wall spaced apart from the inner wall in a radial direction, a space between the inner and outer walls defining a flow passage, and a body positioned between the inner and outer walls, the body traversing the inner and outer walls in an axial direction and attached to an inner surface of the outer wall and an outer surface of the inner wall, the body to detach from the inner and outer surfaces and to at least partially seal the flow passage in response to the outer wall moving relative to the inner wall.Type: ApplicationFiled: December 16, 2021Publication date: June 22, 2023Inventors: Ashish Sharma, Tomasz Edward Berdowski, Maciej Czerwinski, Katarzyna Anna Mikolajczyk, Raymond Floyd Martell, Tomasz Jan Bulsiewicz
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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: 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: 20220055759Abstract: Propulsion engines and methods of accessing components within propulsor cavities of propulsion engines are disclosed. A propulsion engine includes an outer engine housing that includes a propulsor cavity located therein. The propulsor cavity is axially located between a low-pressure compressor and a fan of the propulsion engine. An electric converter is disposed within the propulsor cavity.Type: ApplicationFiled: July 21, 2021Publication date: February 24, 2022Inventors: Miroslaw Czarnik, Tomasz Edward Berdowski, Pawel Zdrojewski, Lukasz Maciej Janczak, Maciej Grunwald
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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
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Publication number: 20190284946Abstract: An inter-stage seal assembly includes annular seal land mounted inwardly of and to seal support ring and pre-swirlers in purge duct extending through land. Purge duct may be bounded by spaced apart duct walls and pre-swirlers include turning vanes in outer exhaust section. Purge duct may include plurality of enclosed purge passages circumferentially disposed around engine centerline and pre-swirlers include curved section in passages. Seal land may be bifurcated having forward and aft seal land sections and purge duct may include purge duct inlet located therebetween. Seal support ring may include flange attached to or integrally and monolithically formed with inner platform attached to nozzle vanes extending across turbine flowpath and exhaust section may be flush with platform. Labyrinth seal teeth mounted to turbine rotor may engage land, purge duct may extend between annular inlets and outlets, inlet may be between adjacent couple of seal teeth.Type: ApplicationFiled: March 6, 2019Publication date: September 19, 2019Inventors: Tomasz Edward Berdowski, Artur Miroslaw Malek, Marcin Piotr Rykala, Adam Kiciak, Mahendran Manoharan, Zbigniew Michal Schabowski, Marcin Kawalkowski