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公开(公告)号：US12007113B2
公开(公告)日：2024-06-11
申请号：US17370080
申请日：2021-07-08
CPC分类号： F23R3/002 , F01D9/023 , F23R3/06 , F23R3/346 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A gas turbine combustion duct includes a duct body and a fluid intake hole. The duct body includes a duct wall defining a plenum for routing a flow of combustion products from a combustor downstream through the gas turbine combustion duct to a turbine section. The fluid intake hole extends from an outward-facing surface to an inward-facing surface through the duct wall for receiving an outside fluid flow into the plenum, and is laterally circumscribed about its entire periphery by a lateral-facing surface. The lateral-facing surface includes a curved surface portion along a shortest path from the inward-facing surface to the outward-facing surface and is free of angled surface transitions along the shortest path between the inward-facing surface and the outward-facing surface. The fluid intake hole is wider at the outward-facing surface than at the inward-facing surface. A boss may define the fluid intake hole and the lateral-facing surface.
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公开(公告)号：US11994294B2
公开(公告)日：2024-05-28
申请号：US17931700
申请日：2022-09-13
CPC分类号： F23R3/06 , F02C7/04 , F23R3/002 , F23R2900/03044
摘要： A combustor includes a skeleton mesh structure having a plurality of structural elements configured to mesh together to form the skeleton mesh structure, each of the plurality of structural elements including a frame and, a plurality of louvers connected to the frame. The combustor also includes an inner liner mounted to the skeleton mesh structure to define a combustion chamber. The inner liner includes a plurality of inner planks mounted to the skeleton mesh structure, each of the plurality of inner planks being mounted to a corresponding one of the plurality of structural elements.
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公开(公告)号：US11988145B2
公开(公告)日：2024-05-21
申请号：US16241187
申请日：2019-01-07
申请人： RTX Corporation
发明人： Dennis M. Moura , Carey Clum
CPC分类号： F02C7/18 , F23R3/16 , F23R3/26 , F23R2900/03044
摘要： According to one embodiment, a gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, the first component including a cooling hole extending from the second surface to the first surface through the first component, wherein the second surface of the first component is oriented relative to a first airflow path such that airflow in the first airflow path separates from the second surface of the first component; and a first fairing secured to the first component proximate the second surface of the first component, the first fairing being configured to redirect airflow in the first airflow path such that the airflow exits the first fairing oriented parallel with the second surface of the first component.
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公开(公告)号：US20230400187A1
公开(公告)日：2023-12-14
申请号：US17805983
申请日：2022-06-08
CPC分类号： F23R3/002 , F23R3/346 , F23R2900/00014 , F23R2900/03044
摘要： A combustor for a gas turbine has a combustor liner including an outer liner and an inner liner, a combustion chamber being defined between the outer liner and the inner liner. The combustion chamber includes a primary combustion zone at an upstream end of the combustion chamber. The combustor also includes an outer liner expanded primary volume portion, and a secondary outer liner portion. One of the outer liner expanded primary volume portion and the secondary outer liner portion is movable to adjust a volume of the primary combustion zone by opening and closing access to the outer liner expanded primary volume portion so as to increase and to decrease the volume of the primary combustion zone.
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公开(公告)号：US20230366555A1
公开(公告)日：2023-11-16
申请号：US17931697
申请日：2022-09-13
CPC分类号： F23R3/60 , F23R3/06 , F23R2900/00017 , F23R2900/03044
摘要： A combustor including a skeleton structure. The combustor further includes at least one liner operably coupled to the skeleton structure to at least partially define a combustion chamber, and a plurality of first planks mounted to a first side of the at least one liner and a plurality of second planks mounted to a second side of the at least one liner. The combustor also includes at least one dilution hole structure provided with a portion of the skeleton structure, and including at least one dilution hole configured to allow fluid to pass therethrough into the combustion chamber.
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公开(公告)号：US11719438B2
公开(公告)日：2023-08-08
申请号：US17201846
申请日：2021-03-15
CPC分类号： F23R3/002 , F23R3/06 , B33Y80/00 , F23R2900/03044
摘要： A liner for a combustor in a gas turbine engine. The liner may include a liner body having a cold side and a hot side. The liner may include a dilution opening and a passage extending through the liner body. The passage may be positioned adjacent the dilution opening. The passage may be angled with respect to an interior surface of the liner body. A dilution flow may flow through the dilution opening from the cold side to the hot side and a secondary flow may flow through the passage from the cold side to the hot side. The secondary flow may exit into the hot side behind the dilution flow and may suppresses wakes formed behind the dilution flow on the hot side of the liner.
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公开(公告)号：US11692708B1
公开(公告)日：2023-07-04
申请号：US17809379
申请日：2022-06-28
CPC分类号： F23R3/14 , F23R3/06 , F23R2900/03044
摘要： A combustor liner for a gas turbine includes a liner that at least partially defines a combustion chamber, and that a plurality of dilution openings therethrough. Each dilution opening includes an outer wall defining an outer perimeter of the dilution opening and defining a dilution opening centerline axis through the dilution opening. A plurality of swirl vanes extend from the outer wall into a dilution airflow passage that extends through the dilution opening. Each of the plurality of swirl vanes extends from the outer wall into the dilution airflow passage at a respective swirl vane angle with respect to the outer wall. The plurality of swirl vanes are arranged in a successive arrangement about the outer wall, and successive respective ones of the plurality of swirl vanes extend from the outer wall at a different swirl vane angle.
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8.发明申请公开(公告)号：US20190219268A1
公开(公告)日：2019-07-18
申请号：US16239911
申请日：2019-01-04
发明人： Dennis M. Moura , Carey Clum
CPC分类号： F23R3/007 , F01D5/189 , F23R2900/03044
摘要： A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection feature integrally formed in the first component and fluidly connecting a flow path located proximate to the second surface of first component to the cooling channel, the lateral flow injection feature being configured to direct airflow from the airflow path through a passageway and into the cooling channel at least partially in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.
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公开(公告)号：US20190128138A1
公开(公告)日：2019-05-02
申请号：US16136313
申请日：2018-09-20
发明人： Robert Krewinkel
CPC分类号： F01D25/12 , F01D5/187 , F01D9/04 , F01D9/065 , F05D2250/141 , F05D2260/201 , F23R3/002 , F23R2900/03044
摘要： A turbomachine, with a flow-conducting assembly, which on a first side serves for the flow-conduction of a first medium, which has a first temperature, and which on a second side is coolable with a second medium, which has a second temperature, that is lower than the first temperature, and with an impingement grille including openings which extend spaced from the flow-conducting assembly, wherein via the openings of the impingement grille the second medium is directable onto the second side of the flow-conducting assembly. In the region of at least some of the openings of the impingement grille, flow-conducting elements for the second medium are formed, which emanating from the impingement grille extend in the direction of the second side of the flow-conducting assembly to be cooled.
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10.发明申请公开(公告)号：US20180355725A1
公开(公告)日：2018-12-13
申请号：US15621394
申请日：2017-06-13
发明人： Victor John MORGAN , Andres Jose GARCIA-CRESPO , Elisabeth Kraus BLACK , George Andrew GERGELY , Jonathan Glenn REED
IPC分类号： F01D5/08
CPC分类号： F01D5/085 , B22F3/1055 , B22F5/009 , B23K1/0018 , B23K26/342 , B23K31/02 , B23K2101/001 , B23K2103/26 , B33Y10/00 , B33Y80/00 , F01D5/147 , F01D5/186 , F01D5/187 , F01D9/023 , F01D9/065 , F01D25/12 , F02K1/822 , F05D2230/22 , F05D2230/31 , F05D2230/51 , F05D2240/11 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F23R3/002 , F23R2900/00018 , F23R2900/03044
摘要： A method of creating a cooling arrangement for a turbine component, and a cooling arrangement are provided. The turbine component includes an interior cooling passage formed therein. The method comprises a step of forming a slot through a sidewall of the turbine component. The method further comprises a step of forming an insert having one or more cooling features and a cavity. The method further comprises a step of positioning the insert within the slot. The method further comprises a step of securing the insert within the slot. The method further comprises a step of forming at least one passage in fluid communication with the internal cooling passage, the insert, and an exterior surface of the turbine component.
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