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公开(公告)号：US20190162072A1
公开(公告)日：2019-05-30
申请号：US15823708
申请日：2017-11-28
Applicant: General Electric Company
Inventor： Alan Joseph Parvis , Dane Michael Dale , Ryan Christian Goff
Abstract: Shrouds and shroud segments for gas turbine engines are provided. In one exemplary aspect, a gas turbine engine includes a first rotor blade stage and a second rotor blade stage. The gas turbine engine also includes a shroud formed from a plurality of shroud segments that each have a body and a vane extending from the body. The vane is disposed within the flow path between the first rotor blade stage and the second rotor blade stage to form at least a portion of a nozzle stage. Further, the body of the shroud segment defines an outer wall of the flow path and spans from the first rotor blade stage to the second rotor blade stage. An impingement baffle segment couples the shroud segment with a casing of the gas turbine engine.
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公开(公告)号：US11571768B2
公开(公告)日：2023-02-07
申请号：US15678510
申请日：2017-08-16
Applicant: General Electric Company
Inventor： Alan Joseph Parvis , Timothy Francis Andrews , Mark Samuel Bailey
IPC: B23K26/382 , B23K26/08 , B23K26/361 , B23K37/04 , B23K101/00 , B23K103/00
Abstract: Systems and methods for machining openings of a component are provided. In one exemplary aspect, a laser system includes features for machining an opening into a component, such as a cooling hole for a CMC component of a gas turbine engine. The component can be oriented in a first position and lasered while oriented in the first position to form a portion of the opening. The component is then oriented to a second position and lasered while oriented in the second position to form another portion of the opening. The component is alternated between the first and second positions until the predetermined geometry of the opening is formed. The component is oriented in the first and second positions such that the laser beam can machine the component without clipping areas that are not desired to be machined.
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公开(公告)号：US10822973B2
公开(公告)日：2020-11-03
申请号：US15823708
申请日：2017-11-28
Applicant: General Electric Company
Inventor： Alan Joseph Parvis , Dane Michael Dale , Ryan Christian Goff
Abstract: Shrouds and shroud segments for gas turbine engines are provided. In one exemplary aspect, a gas turbine engine includes a first rotor blade stage and a second rotor blade stage. The gas turbine engine also includes a shroud formed from a plurality of shroud segments that each have a body and a vane extending from the body. The vane is disposed within the flow path between the first rotor blade stage and the second rotor blade stage to form at least a portion of a nozzle stage. Further, the body of the shroud segment defines an outer wall of the flow path and spans from the first rotor blade stage to the second rotor blade stage. An impingement baffle segment couples the shroud segment with a casing of the gas turbine engine.
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公开(公告)号：US20190054572A1
公开(公告)日：2019-02-21
申请号：US15678510
申请日：2017-08-16
Applicant: General Electric Company
Inventor： Alan Joseph Parvis , Timothy Francis Andrews , Mark Samuel Bailey
IPC: B23K26/382
Abstract: Systems and methods for machining openings of a component are provided. In one exemplary aspect, a laser system includes features for machining an opening into a component, such as a cooling hole for a CMC component of a gas turbine engine. The component can be oriented in a first position and lasered while oriented in the first position to form a portion of the opening. The component is then oriented to a second position and lasered while oriented in the second position to form another portion of the opening. The component is alternated between the first and second positions until the predetermined geometry of the opening is formed. The component is oriented in the first and second positions such that the laser beam can machine the component without clipping areas that are not desired to be machined.
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