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Patent Agency Ranking
公开(公告)号：US10717101B2
公开(公告)日：2020-07-21
申请号：US15898285
申请日：2018-02-16
Applicant: General Electric Company
Abstract: A method of forming a cooling assembly in a turbomachine part is provided. The method includes placing an encapsulated diffuser insert partially into a hole in the turbomachine part. The encapsulated diffuser insert has an unobstructed central passageway with a generally circular cross-section at a first end and an elongated rectangular cross-section at a second end opposing the first end. The second end has a sacrificial cap. A coating step coats the turbomachine part to at least partially encapsulate the encapsulated diffuser insert in a coating. A removing step removes the sacrificial cap to enable air flow through the central passageway. The encapsulated diffuser insert remains in the hole of the turbomachine part and the coating, thereby providing the unobstructed central passageway with a generally circular first end and an elongated rectangular second end adjacent to an outer surface of the turbomachine part.
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公开(公告)号：US11525397B2
公开(公告)日：2022-12-13
申请号：US17008775
申请日：2020-09-01
Applicant: General Electric Company
Inventor： Brendon James Leary , Frederic Woodrow Roberts, Jr. , Ibrahim Sezer , Tyler Christopher Henson
IPC: F02C7/05
Abstract: A gas turbine component includes an ejection circuit for removing debris from cooling air flowing through a gas turbine component. The gas turbine component includes: an impingement insert and a debris ejection circuit. The impingement insert, which is disposed within a cavity in the component, includes an end wall and distribution holes for directing cooling air against a wall of the cavity. The debris ejection circuit includes: a bypass aperture defined in the end wall, which fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel, which fluidly couples the end section of the cavity to the wheelspace cavity or the hot gas path. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.
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公开(公告)号：US11415001B1
公开(公告)日：2022-08-16
申请号：US17198839
申请日：2021-03-11
Applicant: General Electric Company
Abstract: A gas turbine component includes a turbine component having an outer wall and an internal cooling passage; a cooling air supply hole through the outer wall in fluid communication with the internal cooling passage; and a filter mound disposed over the cooling air supply hole. The filter mound includes a filter mound wall projecting from the turbine component and defining an interior of the filter mound. At least one hole in the filter mound wall extending through the filter mound wall is configured to permit cooling air supply to pass therethrough while blocking debris from passing through the interior of the filter mound and clogging the cooling air supply hole in fluid communication with the internal cooling passage. The turbine component and the filter mound are formed during manufacturing of the turbine component.
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公开(公告)号：US20220065165A1
公开(公告)日：2022-03-03
申请号：US17008775
申请日：2020-09-01
Applicant: General Electric Company
Inventor： Brendon James Leary , Frederic Woodrow Roberts, JR. , Ibrahim Sezer , Tyler Christopher Henson
IPC: F02C7/05
Abstract: A gas turbine component includes an ejection circuit for removing debris from cooling air flowing through a gas turbine component. The gas turbine component includes: an impingement insert and a debris ejection circuit. The impingement insert, which is disposed within a cavity in the component, includes an end wall and distribution holes for directing cooling air against a wall of the cavity. The debris ejection circuit includes: a bypass aperture defined in the end wall, which fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel, which fluidly couples the end section of the cavity to the wheelspace cavity or the hot gas path. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.
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公开(公告)号：US20190255550A1
公开(公告)日：2019-08-22
申请号：US15898285
申请日：2018-02-16
Applicant: General Electric Company
Abstract: A method of forming a cooling assembly in a turbomachine part is provided. The method includes placing an encapsulated diffuser insert partially into a hole in the turbomachine part. The encapsulated diffuser insert has an unobstructed central passageway with a generally circular cross-section at a first end and an elongated rectangular cross-section at a second end opposing the first end. The second end has a sacrificial cap. A coating step coats the turbomachine part to at least partially encapsulate the encapsulated diffuser insert in a coating. A removing step removes the sacrificial cap to enable air flow through the central passageway. The encapsulated diffuser insert remains in the hole of the turbomachine part and the coating, thereby providing the unobstructed central passageway with a generally circular first end and an elongated rectangular second end adjacent to an outer surface of the turbomachine part.
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