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公开(公告)号：US11549437B2
公开(公告)日：2023-01-10
申请号：US17178418
申请日：2021-02-18
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Hamdullah Ozogul , Atul Verma , Amy Kujala , Michael Wedig , Ryan Meyer , Bradley Culbertson
Abstract: A combustor for a gas turbine engine includes an outer liner having a first end interconnected to an opposite second end by an outer liner wall composed of a plurality of outer segments. The inner liner has a first inner end interconnected to an opposite second inner end by an inner liner wall composed of a plurality of inner segments. The outer liner wall and the inner liner wall define a combustion chamber, and each of the outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis. The outer wall segments includes a first segment, a second segment that extends at a second angle relative to the first segment, which is less than a third angle defined between the second segment and a third segment and is substantially the same as a fourth angle defined between the third segment and a fourth segment.
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公开(公告)号：US11519604B2
公开(公告)日：2022-12-06
申请号：US17305202
申请日：2021-07-01
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Nagaraja S. Rudrapatna , Atul Verma , David Chou , Christopher Zollars
IPC: F23R3/04
Abstract: A combustor for a gas turbine engine includes a liner having a first surface, a second surface opposite the first surface, and defining a plurality of effusion cooling holes. At least one of the effusion cooling holes includes an inlet section and a converging section downstream of the inlet section. The at least one of the effusion cooling holes includes a metering section downstream of the converging section. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface. The inlet section, the converging section, the metering section and the outlet section extend along a longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.
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公开(公告)号：US20220260016A1
公开(公告)日：2022-08-18
申请号：US17178418
申请日：2021-02-18
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Hamdullah Ozogul , Atul Verma , Amy Kujala , Michael Wedig , Ryan Meyer , Bradley Culbertson
Abstract: A combustor for a gas turbine engine includes an outer liner having a first end interconnected to an opposite second end by an outer liner wall composed of a plurality of outer segments. The inner liner has a first inner end interconnected to an opposite second inner end by an inner liner wall composed of a plurality of inner segments. The outer liner wall and the inner liner wall define a combustion chamber, and each of the outer wall segments extend at an angle of at least 40 degrees relative to a longitudinal axis. The outer wall segments includes a first segment, a second segment that extends at a second angle relative to the first segment, which is less than a third angle defined between the second segment and a third segment and is substantially the same as a fourth angle defined between the third segment and a fourth segment.
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公开(公告)号：US20210325045A1
公开(公告)日：2021-10-21
申请号：US17305202
申请日：2021-07-01
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Nagaraja S. Rudrapatna , Atul Verma , David Chou , Christopher Zollars
IPC: F23R3/04
Abstract: A combustor for a gas turbine engine includes a liner having a first surface, a second surface opposite the first surface, and defining a plurality of effusion cooling holes. At least one of the effusion cooling holes includes an inlet section and a converging section downstream of the inlet section. The at least one of the effusion cooling holes includes a metering section downstream of the converging section. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface. The inlet section, the converging section, the metering section and the outlet section extend along a longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.
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公开(公告)号：US10775044B2
公开(公告)日：2020-09-15
申请号：US16172383
申请日：2018-10-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Atul Verma , Sunil James , Hamdullah Ozogul , John Gintert
IPC: F23R3/00
Abstract: A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.
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Patent Agency Ranking
公开(公告)号：US20200166211A1
公开(公告)日：2020-05-28
申请号：US16200848
申请日：2018-11-27
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Nagaraja S. Rudrapatna , Atul Verma , David Chou , Christopher Zollars
IPC: F23R3/04
Abstract: A combustor for a gas turbine engine includes a first liner having a first surface, a second surface opposite the first surface, and a wall having a thickness defined between the first surface and the second surface. The first liner defines a plurality of effusion cooling holes, and at least one of the effusion cooling holes includes an inlet section spaced apart from the first surface, and a converging section downstream of the inlet section. The inlet section and the converging section are each defined so as to be outside of the thickness. The at least one of the effusion cooling holes includes a metering section downstream of the converging section and a portion of the metering section is defined within the thickness. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface.
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公开(公告)号：US20200132304A1
公开(公告)日：2020-04-30
申请号：US16172383
申请日：2018-10-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Atul Verma , Sunil James , Hamdullah Ozogul , John Gintert
Abstract: A hot section part of a turbine engine configured to be exposed to hot gases includes a first wall, a second wall, a plurality of pedestals, a plurality of impingement cooling holes, and a plurality of effusion cooling passages. The walls are spaced apart to form an intervening cavity, and each pedestal extends through the intervening cavity. The impingement cooling holes extend through the second wall to admit a flow of cooling air into the intervening cavity. Each effusion cooling passage is associated with a different one of the plurality of pedestals and is disposed at a predetermined angle relative to its associated principal axis. A portion of the flow of cooling air admitted to the intervening cavity is directed through at least a portion of each of the plurality of pedestals and onto the first wall inner surface.
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公开(公告)号：US12085279B1
公开(公告)日：2024-09-10
申请号：US18313578
申请日：2023-05-08
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jon Anderson , Nagaraja Rudrapatna , Carlos Vallellanes , Atul Verma
CPC classification number: F23R3/002 , F02C7/18 , F23R3/06 , F05D2220/32 , F05D2240/35 , F05D2260/202 , F05D2260/22141
Abstract: A combustor for a gas turbine engine includes a combustor liner with a wall defining a combustion chamber. The wall has an inner surface facing the combustion chamber and an outer surface across the wall from the inner surface. Fins are disposed on the outer surface. The wall defines air admission holes that extend through the wall from the outer surface to the inner surface. The wall also defines film cooling holes that extend through the wall from the outer surface to the inner surface. The fins are disposed in areas of the outer surface between the film cooling holes and the air admission holes to cool areas that would otherwise result in hot spots.
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公开(公告)号：US11959401B1
公开(公告)日：2024-04-16
申请号：US18189739
申请日：2023-03-24
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shakeel Nasir , Atul Verma , Jeffrey Krise , Doni Tapederi , Jacob Salai , Rodolphe Dudebout
CPC classification number: F01D9/04 , F02C3/04 , F23R3/26 , F05D2220/323 , F05D2240/127 , F05D2260/60
Abstract: A deswirl system for a gas turbine engine includes a deswirl shroud, and at least one deswirl vane having a leading end and a trailing end. The deswirl system includes a deswirl hub spaced apart from the deswirl shroud by the at least one deswirl vane. The deswirl hub includes a hub body that extends at a first angle and a hub extension that extends beyond the trailing end of the at least one deswirl vane. The hub extension extends from the hub body at a second angle, and the first angle is different than the second angle.
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公开(公告)号：US11085641B2
公开(公告)日：2021-08-10
申请号：US16200848
申请日：2018-11-27
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Rodolphe Dudebout , Nagaraja S. Rudrapatna , Atul Verma , David Chou , Christopher Zollars
IPC: F23R3/04
Abstract: A combustor for a gas turbine engine includes a first liner having a first surface, a second surface opposite the first surface, and a wall having a thickness defined between the first surface and the second surface. The first liner defines a plurality of effusion cooling holes, and at least one of the effusion cooling holes includes an inlet section spaced apart from the first surface, and a converging section downstream of the inlet section. The inlet section and the converging section are each defined so as to be outside of the thickness. The at least one of the effusion cooling holes includes a metering section downstream of the converging section and a portion of the metering section is defined within the thickness. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface.
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