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公开(公告)号：US20230167743A1
公开(公告)日：2023-06-01
申请号：US17538730
申请日：2021-11-30
Applicant: Rolls-Royce Corporation
Inventor： Brett Barker , Eric Koenig
CPC classification number: F01D5/186 , F01D5/147 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2260/202
Abstract: An airfoil, such as a vane or a blade for a gas turbine engine, may be provided, where the airfoil comprises: a platform; a spar; a fillet; and a coversheet. The spar may include a passageway inside of the spar for a cooling fluid, a pedestal on an outer surface of the spar, and a spar hole configured to direct the cooling fluid from the passageway to the outer surface of the spar. The spar may be coupled or integral to the platform by the fillet located at the intersection of the platform and the spar. An inner surface of the coversheet may be positioned on the pedestal of the spar. The fillet and/or the coversheet includes a protrusion extending along the edge of the coversheet. The protrusion, along with the pedestal and the outer surface of the spar, define a purge groove. The purge groove includes a purge groove outlet and the purge groove and the purge groove outlet together form a cooling path for cooling fluid to flow onto the platform.
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公开(公告)号：US11598215B1
公开(公告)日：2023-03-07
申请号：US17501277
申请日：2021-10-14
Applicant: Rolls-Royce Corporation
Inventor： Brett Barker
IPC: F01D5/18
Abstract: A dual-wall airfoil configured for coolant transfer includes a spar having a pressure side wall and a suction side wall each including raised features on an outer surface thereof. An interior of the spar includes coolant cavities. An inner surface of a pressure side coversheet is in contact with the raised features on the outer surface of the pressure side wall so as to define pressure side flow pathways between the pressure side wall and the pressure side coversheet, and an inner surface of a suction side coversheet is in contact with the raised features on the outer surface of the suction side wall so as to define suction side flow pathways between the suction side wall and the suction side coversheet. The pressure side flow pathways and/or the suction side flow pathways include cooling circuit(s) configured to transfer coolant between the coolant cavities.
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公开(公告)号：US20210215051A1
公开(公告)日：2021-07-15
申请号：US16741609
申请日：2020-01-13
Applicant: Rolls-Royce Corporation
Inventor： Eric Koenig , Brett Barker
IPC: F01D5/18
Abstract: A system includes an air foil positionable in a combustion flow path of a combustion turbine. A shank may be integrally formed with the air foil, and the platform may be integrally formed with the shank. The platform includes linear fluid passageways, access ducts penetrating a wedge face surface of the platform, and outlet apertures formed in a radially outward surface of the platform. The outlet apertures are in fluid communication with respective linear fluid passageways such that fluid flowing through the respective linear fluid passageways is discharged from the outlet apertures into the combustion flow path. The platform also includes plugs is disposed in respective access ducts to form a fluid tight seal and be positioned in at least one of the respective linear fluid passageways. Fluid flowing through the respective linear fluid passageways flows away from a respective plug for discharge from a respective outlet aperture.
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公开(公告)号：US20200080426A1
公开(公告)日：2020-03-12
申请号：US16580784
申请日：2019-09-24
Applicant: Rolls-Royce Corporation
Inventor： Brett Barker , Bruce Varney , Brian Shoemaker , Charles Bulgrin
Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.
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公开(公告)号：US11773728B2
公开(公告)日：2023-10-03
申请号：US17538730
申请日：2021-11-30
Applicant: Rolls-Royce Corporation
Inventor： Brett Barker , Eric Koenig
CPC classification number: F01D5/186 , F01D5/147 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2260/202
Abstract: An airfoil, such as a vane or a blade for a gas turbine engine, may be provided. The airfoil may include a platform; a spar; a fillet; and a coversheet. The spar may include a passageway inside of the spar for a cooling fluid, a pedestal on an outer surface of the spar, and a spar hole configured to direct the cooling fluid from the passageway to the outer surface of the spar. The fillet may be located at the intersection of the platform and the spar, and may couple the spar to the platform. The fillet and/or the coversheet may include a protrusion extending along the edge of the coversheet. The protrusion, along with the pedestal and the outer surface of the spar, may define a purge groove. The purge groove and a purge groove outlet may form a cooling path for cooling fluid to flow onto the platform.
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Patent Agency Ranking
公开(公告)号：US20230175403A1
公开(公告)日：2023-06-08
申请号：US18162108
申请日：2023-01-31
Applicant: Rolls-Royce Corporation
Inventor： Brett Barker
IPC: F01D5/18
CPC classification number: F01D5/181 , F05D2240/30 , F05D2260/20 , F05D2220/32
Abstract: A dual-wall airfoil configured for coolant transfer includes a spar having a pressure side wall and a suction side wall each including raised features on an outer surface thereof. An interior of the spar includes coolant cavities. An inner surface of a pressure side coversheet is in contact with the raised features on the outer surface of the pressure side wall so as to define pressure side flow pathways between the pressure side wall and the pressure side coversheet, and an inner surface of a suction side coversheet is in contact with the raised features on the outer surface of the suction side wall so as to define suction side flow pathways between the suction side wall and the suction side coversheet. The pressure side flow pathways and/or the suction side flow pathways include cooling circuit(s) configured to transfer coolant between the coolant cavities.
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公开(公告)号：US20230141484A1
公开(公告)日：2023-05-11
申请号：US17520067
申请日：2021-11-05
Inventor： Brett Barker , Eric Koenig , Jerry Layne , Jeffrey F. Rhodes
CPC classification number: F01D5/187 , F01D5/147 , F05D2240/303 , F05D2240/304 , F05D2260/202 , F05D2260/213 , F05D2260/2214
Abstract: Airfoils and methods of cooling an airfoil are provided. The airfoil may comprise a spar; a coversheet on the spar; and a dual feed circuit between the spar and the coversheet. The dual feed circuit may include a first dam, a second dam spaced apart from the first dam along the chord axis of the spar, a first inlet disposed adjacent to the first dam, a second inlet disposed adjacent to the second dam, a circuit outlet disposed between the first inlet and the second inlet, and a plurality of diamond and/or hexagonal pedestals disposed on an outer surface of the spar. The diamond and/or hexagonal pedestals may form a plurality of cooling channels between the first inlet, the second inlet, and the circuit outlet. There may be no other circuit inlets are located between the first inlet and the second inlet.
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公开(公告)号：US11536143B1
公开(公告)日：2022-12-27
申请号：US17559803
申请日：2021-12-22
Inventor： Jack Moody , Jerry Layne , Jeffrey F. Rhodes , Brett Barker , Eric Koenig
Abstract: An endwall assembly disposed at one end of a vane assembly may comprise an endwall spar that includes an cold side, an hot side, a leading edge, a trailing edge, and an axis extending from the leading edge to the trailing edge perpendicular to the leading edge. The endwall assembly may include a coversheet on the hot side of the endwall spar and a cooling channel that includes a cooling fluid inlet disposed in the endwall spar, and a cooling fluid outlet. The endwall assembly may include a structure protruding from the cold side of the endwall spar, wherein the structure is located between the cooling fluid inlet and the cooling fluid outlet along the axis; and a cooling fluid source cavity on the cold side of the wall, the cooling fluid source cavity in fluid communication with the cooling fluid channel via the cooling fluid inlet.
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公开(公告)号：US11225873B2
公开(公告)日：2022-01-18
申请号：US16741609
申请日：2020-01-13
Applicant: Rolls-Royce Corporation
Inventor： Eric Koenig , Brett Barker
IPC: F01D5/18
Abstract: A system includes an air foil positionable in a combustion flow path of a combustion turbine. A shank may be integrally formed with the air foil, and the platform may be integrally formed with the shank. The platform includes linear fluid passageways, access ducts penetrating a wedge face surface of the platform, and outlet apertures formed in a radially outward surface of the platform. The outlet apertures are in fluid communication with respective linear fluid passageways such that fluid flowing through the respective linear fluid passageways is discharged from the outlet apertures into the combustion flow path. The platform also includes plugs is disposed in respective access ducts to form a fluid tight seal and be positioned in at least one of the respective linear fluid passageways. Fluid flowing through the respective linear fluid passageways flows away from a respective plug for discharge from a respective outlet aperture.
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公开(公告)号：US10450873B2
公开(公告)日：2019-10-22
申请号：US15664996
申请日：2017-07-31
Applicant: Rolls-Royce Corporation
Inventor： Brett Barker , Bruce Varney , Brian Shoemaker , Charles Bulgrin
Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.
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