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公开(公告)号：US20220260017A1
公开(公告)日：2022-08-18
申请号：US17178429
申请日：2021-02-18
Applicant: General Electric Company
Inventor： Benjamin Johannes Seppala , Kenneth Jay Moore , Thomas Ryan Wallace
Abstract: A gas turbine engine having a fluid transfer connection is provided. The gas turbine engine includes a first component configured to channel a flow of air from a portion of the gas turbine engine; a second component configured to receive the flow of air from the first component, wherein the first component and the second component are movable relative to one another; a sleeve portion disposed between the first component and the second component; and a spoolie device disposed within the sleeve portion, the spoolie device having elliptical shaped opposing ends, wherein the spoolie device bridges the first component and the second component to channel the flow of air from the first component to the second component.
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公开(公告)号：US11359498B2
公开(公告)日：2022-06-14
申请号：US16749146
申请日：2020-01-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Joseph Kreitzer , Bradford Alan Tracey , Michael Everitt Isenberg , Thomas Joseph Lipinski , Scott Alan Schimmels , Kenneth Jay Moore
Abstract: An airfoil assembly for a turbine engine can include an airfoil having an outer wall bounding an interior, and an insert located within the interior with a space between the insert and airfoil outer wall. A cooling hole can pass through the insert with an outlet fluidly coupled to the space between the insert and outer wall.
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公开(公告)号：US11692485B2
公开(公告)日：2023-07-04
申请号：US17178429
申请日：2021-02-18
Applicant: General Electric Company
Inventor： Benjamin Johannes Seppala , Kenneth Jay Moore , Thomas Ryan Wallace
CPC classification number: F02C7/16 , F01D9/06 , F01D25/12 , F05D2220/32 , F05D2260/20 , F05D2260/60
Abstract: A gas turbine engine having a fluid transfer connection is provided. The gas turbine engine includes a first component configured to channel a flow of air from a portion of the gas turbine engine; a second component configured to receive the flow of air from the first component, wherein the first component and the second component are movable relative to one another; a sleeve portion disposed between the first component and the second component; and a spoolie device disposed within the sleeve portion, the spoolie device having elliptical shaped opposing ends, wherein the spoolie device bridges the first component and the second component to channel the flow of air from the first component to the second component.
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Patent Agency Ranking
公开(公告)号：US20200277863A1
公开(公告)日：2020-09-03
申请号：US16749146
申请日：2020-01-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Joseph Kreitzer , Bradford Alan Tracey , Michael Everitt Isenberg , Thomas Joseph Lipinski , Scott Alan Schimmels , Kenneth Jay Moore
Abstract: An airfoil assembly for a turbine engine can include an airfoil having an outer wall bounding an interior, and an insert located within the interior with a space between the insert and airfoil outer wall. A cooling hole can pass through the insert with an outlet fluidly coupled to the space between the insert and outer wall.
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公开(公告)号：US20170234155A1
公开(公告)日：2017-08-17
申请号：US15041524
申请日：2016-02-11
Applicant: General Electric Company
Inventor： Thomas Lipinski , Donald George LaChapelle , Kenneth Jay Moore , Bradford Tracey , Stephen Joseph Waymeyer
CPC classification number: F01D25/14 , F01D9/065 , F01D11/005 , F01D17/085 , F01D17/105 , F01D17/145 , F01D25/12 , F01D25/145 , F01D25/162 , F01D25/24 , F02C7/12 , F05D2220/32 , F05D2260/20 , Y02T50/675
Abstract: A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops coupled to the outer ring. The plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity of the outer ring.
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公开(公告)号：US10570751B2
公开(公告)日：2020-02-25
申请号：US15820613
申请日：2017-11-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Joseph Kreitzer , Bradford Alan Tracey , Michael Everitt Isenberg , Thomas Joseph Lipinski , Scott Alan Schimmels , Kenneth Jay Moore
Abstract: An airfoil assembly for a turbine engine can include an airfoil having an outer wall bounding an interior, and an insert located within the interior with a space between the insert and airfoil outer wall. A cooling hole can pass through the insert with an outlet fluidly coupled to the space between the insert and outer wall.
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公开(公告)号：US20190153875A1
公开(公告)日：2019-05-23
申请号：US15820613
申请日：2017-11-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Joseph Kreitzer , Bradford Alan Tracey , Michael Everitt Isenberg , Thomas Joseph Lipinski , Scott Alan Schimmels , Kenneth Jay Moore
Abstract: An airfoil assembly for a turbine engine can include an airfoil having an outer wall bounding an interior, and an insert located within the interior with a space between the insert and airfoil outer wall. A cooling hole can pass through the insert with an outlet fluidly coupled to the space between the insert and outer wall.
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公开(公告)号：US10151217B2
公开(公告)日：2018-12-11
申请号：US15041524
申请日：2016-02-11
Applicant: General Electric Company
Inventor： Thomas Lipinski , Donald George LaChapelle , Kenneth Jay Moore , Bradford Tracey , Stephen Joseph Waymeyer
IPC: F01D25/14 , F01D11/00 , F01D17/08 , F01D17/10 , F01D17/14 , F01D25/12 , F01D25/24 , F01D9/06 , F01D25/16 , F02C7/12
Abstract: A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops coupled to the outer ring. The plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity of the outer ring.
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