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1.发明授权公开(公告)号：US10677084B2
公开(公告)日：2020-06-09
申请号：US15899756
申请日：2018-02-20
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , Kent L. Kime , Blake Petersen , Luke Zurmehly
Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.
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2.发明申请公开(公告)号：US20170211586A1
公开(公告)日：2017-07-27
申请号：US15006551
申请日：2016-01-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Raymond Gage , Bruce David Reynolds , Jeffrey D. Harrison , Michael Todd Barton , Mahmoud Mansour , Kent L. Kime
CPC classification number: F04D29/4206 , F02C3/08 , F02C6/08 , F04D29/284 , F04D29/444 , F04D29/582 , F05D2220/32 , F05D2240/128 , F05D2240/30 , F05D2260/20 , Y02T50/671
Abstract: Embodiments of an impeller shroud support for disposition around an impeller are provided, as are embodiments of gas turbine engine including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body, a support arm joined to and extending around the shroud body, and a plurality of Mid-Impeller Bleed (MIB) flow passages. Each MIB flow passage includes, in turn, an inlet formed in the shroud body and configured to receive bleed air extracted from the impeller, a throat portion, an outlet formed in the support arm and through which the bleed air is discharged, and a curved intermediate section between the inlet and the outlet. During usage of the impeller shroud support, the curved intermediate section turns the bleed air flowing through the MIB passage in a radially outward direction prior to discharge from the outlet of the MIB flow passage.
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公开(公告)号：US20210140343A1
公开(公告)日：2021-05-13
申请号：US17101073
申请日：2020-11-23
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , Kent L. Kime , Blake Petersen , Luke Zurmehly
Abstract: A shroud assembly for a gas turbine engine includes a shroud support and a plurality of shroud segments that are attached to the shroud support. The shroud segment includes an internal cooling passage.
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4.发明申请公开(公告)号：US20210003025A1
公开(公告)日：2021-01-07
申请号：US16831045
申请日：2020-03-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , Kent L. Kime , Blake Petersen , Luke Zurmehly
Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.
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Patent Agency Ranking
5.发明申请公开(公告)号：US20180363499A1
公开(公告)日：2018-12-20
申请号：US15899780
申请日：2018-02-20
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , Kent L. Kime , Blake Petersen , Luke Zurmehly
Abstract: A shroud assembly for a gas turbine engine includes a shroud support and a plurality of shroud segments that are attached to the shroud support. The shroud segment includes an internal cooling passage.
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6.发明授权公开(公告)号：US11181006B2
公开(公告)日：2021-11-23
申请号：US16831045
申请日：2020-03-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , Kent L. Kime , Blake Petersen , Luke Zurmehly
Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.
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公开(公告)号：US10900378B2
公开(公告)日：2021-01-26
申请号：US15899780
申请日：2018-02-20
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , Kent L. Kime , Blake Petersen , Luke Zurmehly
Abstract: A shroud assembly for a gas turbine engine includes a shroud support and a plurality of shroud segments that are attached to the shroud support. The shroud segment includes an internal cooling passage.
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公开(公告)号：US10359051B2
公开(公告)日：2019-07-23
申请号：US15006551
申请日：2016-01-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Raymond Gage , Bruce David Reynolds , Jeffrey D. Harrison , Michael Todd Barton , Mahmoud Mansour , Kent L. Kime
Abstract: Embodiments of an impeller shroud support for disposition around an impeller are provided, as are embodiments of gas turbine engine including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body, a support arm joined to and extending around the shroud body, and a plurality of Mid-Impeller Bleed (MIB) flow passages. Each MIB flow passage includes, in turn, an inlet formed in the shroud body and configured to receive bleed air extracted from the impeller, a throat portion, an outlet formed in the support arm and through which the bleed air is discharged, and a curved intermediate section between the inlet and the outlet. During usage of the impeller shroud support, the curved intermediate section turns the bleed air flowing through the MIB passage in a radially outward direction prior to discharge from the outlet of the MIB flow passage.
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9.发明申请公开(公告)号：US20180363486A1
公开(公告)日：2018-12-20
申请号：US15899756
申请日：2018-02-20
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , Kent L. Kime , Blake Petersen , Luke Zurmehly
CPC classification number: F01D11/08 , F01D9/04 , F01D11/005 , F01D11/122 , F01D25/12 , F01D25/246 , F05D2240/11 , F05D2240/55 , F05D2240/56 , F05D2260/201 , F05D2260/204
Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.
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