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公开(公告)号：US20210222879A1
公开(公告)日：2021-07-22
申请号：US16746432
申请日：2020-01-17
IPC分类号： F23R3/00
摘要： A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. The combustor further includes a bulkhead extending between the inner shell and the outer shell. The combustor further includes a liner panel mounted to one of the inner shell and the outer shell aft of the bulkhead. The liner panel includes a first section including a first plurality of effusion holes. A first portion of the first plurality of effusion holes extends in a substantially circumferential direction. A second portion of the first plurality of effusion holes, disposed forward of the first portion, transitions from the substantially circumferential direction toward a substantially forward direction. A third portion of the first plurality of effusion holes, disposed aft of the first portion, transitions from the substantially circumferential direction to a substantially aft direction.
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公开(公告)号：US20210207807A1
公开(公告)日：2021-07-08
申请号：US16736340
申请日：2020-01-07
IPC分类号： F23R3/00
摘要： A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. The combustor further includes a bulkhead extending between the inner shell and the outer shell. The bulkhead includes a plurality of impingement cooling rings. Each impingement cooling ring of the plurality of impingement cooling rings includes a plurality of impingement cooling holes extending through the bulkhead. The combustor further includes a heat shield panel mounted to the bulkhead so as to define an impingement cooling chamber between the bulkhead and the heat shield panel. The heat shield panel further includes a radial portion between a perimeter and an opening, with respect to an opening center axis, which is free of penetrations. The plurality of impingement cooling holes of each of the plurality of impingement cooling rings are directed toward the radial portion of the heat shield panel.
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公开(公告)号：US11326518B2
公开(公告)日：2022-05-10
申请号：US16751494
申请日：2020-01-24
发明人： Maleek E. Wedderburn , Nurhak Erbas-Sen , John W. Mubeezi , Fumitaka Ichihashi , Roger O. Coffey
摘要： A combustor panel arrangement for a gas turbine engine. The combustor panel arrangement includes a first combustor panel that has a first edge. A second combustor panel has a second edge facing the first edge. A first plurality of effusion holes extend through the first edge towards the second edge along a corresponding one of a first plurality of flow paths. A second plurality of effusion holes extend through the second edge along a corresponding one of a second plurality flow paths towards the first edge. The first plurality of flow paths and the second plurality of flow paths are non-intersecting.
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公开(公告)号：US11293638B2
公开(公告)日：2022-04-05
申请号：US16549722
申请日：2019-08-23
摘要： A combustor for a gas turbine engine includes an annular shell, an annular bulkhead connected to the shell, and a heat shield panel. The heat shield panel has a first surface facing a combustion chamber and a second surface opposite the first surface. The heat shield panel is mounted to the bulkhead and defines a cooling chamber between the bulkhead and the heat shield panel. The heat shield panel has a wall extending from the heat shield panel toward the bulkhead around at least a portion of a periphery of the heat shield panel. The wall includes a circumferential wall portion including at least one cooling air passage extending between the cooling chamber and a cavity defined between the circumferential wall portion and the shell. The at least one cooling air passage is configured to purge the cavity by directing a first cooling air stream from the cooling chamber into the cavity.
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公开(公告)号：US20210055000A1
公开(公告)日：2021-02-25
申请号：US16549722
申请日：2019-08-23
摘要： A combustor for a gas turbine engine includes an annular shell, an annular bulkhead connected to the shell, and a heat shield panel. The heat shield panel has a first surface facing a combustion chamber and a second surface opposite the first surface. The heat shield panel is mounted to the bulkhead and defines a cooling chamber between the bulkhead and the heat shield panel. The heat shield panel has a wall extending from the heat shield panel toward the bulkhead around at least a portion of a periphery of the heat shield panel. The wall includes a circumferential wall portion including at least one cooling air passage extending between the cooling chamber and a cavity defined between the circumferential wall portion and the shell. The at least one cooling air passage is configured to purge the cavity by directing a first cooling air stream from the cooling chamber into the cavity.
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公开(公告)号：US10808936B2
公开(公告)日：2020-10-20
申请号：US16020736
申请日：2018-06-27
发明人： Steven D Porter , John T Ols , Fumitaka Ichihashi
摘要： A heat shield panel for a gas turbine engine combustor may comprise a perimetrical rail extending at least partially around a perimeter of the heat shield panel and defining a main backside cavity, a plurality of air admittance holes, each air admittance hole extending along a hole axis, and a midrail dividing the main backside cavity into a first backside cavity and a second backside cavity, wherein at least a portion of the midrail is axially offset from at least one of the hole axes.
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公开(公告)号：US20190285276A1
公开(公告)日：2019-09-19
申请号：US15921376
申请日：2018-03-14
IPC分类号： F23R3/00
摘要： A combustor panel may comprise a surface extending from a first end of the combustor panel to a second end of the combustor panel opposite the first end. A first rail located proximate the first end may extend from the surface of the combustor panel. The first rail may define a plurality of channels. The first rail may be formed a preselected distance away from the first end of the combustor panel.
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公开(公告)号：US11209162B2
公开(公告)日：2021-12-28
申请号：US16725116
申请日：2019-12-23
发明人： Fumitaka Ichihashi
摘要： A gas turbine engine component having a first surface in communication with a core airflow. The gas turbine engine component further includes a second surface, different than the first surface, for cooling the first surface. The gas turbine engine component further includes a heat transfer augmentor extending from the second surface. The gas turbine engine component further includes a heat transfer augmentor effusion hole extending through the gas turbine engine component from a sidewall of the heat transfer augmentor to the first surface.
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公开(公告)号：US20200003423A1
公开(公告)日：2020-01-02
申请号：US16020736
申请日：2018-06-27
发明人： Steven D Porter , John T Ols , Fumitaka Ichihashi
摘要： A heat shield panel for a gas turbine engine combustor may comprise a perimetrical rail extending at least partially around a perimeter of the heat shield panel and defining a main backside cavity, a plurality of air admittance holes, each air admittance hole extending along a hole axis, and a midrail dividing the main backside cavity into a first backside cavity and a second backside cavity, wherein at least a portion of the midrail is axially offset from at least one of the hole axes.
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公开(公告)号：US11561007B2
公开(公告)日：2023-01-24
申请号：US16725049
申请日：2019-12-23
发明人： Fumitaka Ichihashi
摘要： A combustor liner for a gas turbine engine, the combustor liner including a panel configured to at least partially define a combustion chamber. The combustor liner further includes a shell configured to mount to the panel and form a gap between the panel and the shell. The panel includes a stud and a plurality of a stand-off pins proximate to the stud defining a cavity therebetween. The shell includes a plurality of angled impingement holes located away from the cavity but extending through the shell at an orientation such that cooling air passing through the angled impingement holes is directed towards the cavity between adjacent stand-off pins and at an acute angle relative to the stud.
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