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公开(公告)号：US10774655B2
公开(公告)日：2020-09-15
申请号：US15919253
申请日：2018-03-13
发明人： Brandon W. Spangler , Gina Cavallo
摘要： A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a wall that extends about a cooling cavity. The cooling cavity is a dual-fed cavity that is fed from at least two different locations. A rib separates the cooling cavity into a first portion and a second portion that is fluidly isolated from the first portion. The component is an airfoil. The first portion is fed with a first cooling fluid from a first coolant source, and the second portion is fed with a second, different cooling fluid from a second coolant source. The first and second coolant sources are separate and distinct from the component.
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公开(公告)号：US09771814B2
公开(公告)日：2017-09-26
申请号：US14641470
申请日：2015-03-09
发明人： Brandon W. Spangler , Ky H. Vu , Jeffrey J. DeGray , Ryan Alan Waite , Gina Cavallo , Thomas P. Dziuba
CPC分类号： F01D9/041 , F01D5/02 , F01D5/186 , F01D5/189 , F01D9/065 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2230/21 , F05D2230/642 , F05D2240/126 , F05D2240/80 , F05D2260/20 , F05D2260/30 , Y02T50/676
摘要： A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.
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公开(公告)号：US10041374B2
公开(公告)日：2018-08-07
申请号：US14665182
申请日：2015-03-23
发明人： Brandon W. Spangler , Ky H. Vu , Gina Cavallo
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, a platform and a feed cavity that feeds a cooling fluid inside of the platform. The feed cavity includes a leg portion and a main body portion that extends from the leg portion inside of the platform. A cooling cavity is inside the platform and in fluid communication with the feed cavity.
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公开(公告)号：US20160265372A1
公开(公告)日：2016-09-15
申请号：US14641470
申请日：2015-03-09
发明人： Brandon W. Spangler , Ky H. Vu , Jeffrey J. DeGray , Ryan Alan Waite , Gina Cavallo , Thomas P. Dziuba
CPC分类号： F01D9/041 , F01D5/02 , F01D5/186 , F01D5/189 , F01D9/065 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2230/21 , F05D2230/642 , F05D2240/126 , F05D2240/80 , F05D2260/20 , F05D2260/30 , Y02T50/676
摘要： A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.
摘要翻译： 燃气涡轮发动机部件组件包括相对于发动机中心轴线与第一部件周向间隔开的第一部件和第二部件。 第一挡板与第一部件相关联。 第二挡板与第二部件相关联。 第一和第二挡板中的每一个包括至少一个径向挡板。 在第一和第二挡板之间形成间隙以限定冷却空气入口。 第一盖板与第一挡板相关联以覆盖间隙的第一部分。 第二盖板与第二挡板相关联以覆盖间隙的第二部分。 第一和第二盖板彼此分开，并且包括至少一个盖板径向突片，其与相关联的至少一个挡板径向突片配合，以防止第一和第二挡板与第一和第二盖板之间的泄漏间隙。
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公开(公告)号：US20170114798A1
公开(公告)日：2017-04-27
申请号：US14924210
申请日：2015-10-27
发明人： Brandon W. Spangler , Gina Cavallo
CPC分类号： F04D29/582 , F01D5/186 , F01D9/065 , F01D25/12 , F02C7/18 , F04D29/164 , F04D29/526 , F04D29/542 , F04D29/644 , F05D2220/32 , F05D2230/10 , F05D2240/11 , F05D2240/12 , F05D2240/15 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/672 , Y02T50/675 , Y02T50/676
摘要： A surface structure having a filmhole pattern is disclosed. The filmhole pattern may be an offset herringbone pattern. For instance, the surface structure may have rows of filmholes arranged in filmrows, each filmrow divided into groups of filmholes. A first group may be oriented to direct cooling air generally outward over a surface of the surface structure and a second group may be oriented to direct cooling air generally inward over a surface of the surface structure. Between the first group and the second group of filmholes in each filmrow, a transition region exists. The adjacent filmrows are arranged to enhance the effectiveness of the convective cooling proximate to the transition regions by causing each filmrow to direct cooling air over the transition region of an adjacent filmrow.
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公开(公告)号：US20160258306A1
公开(公告)日：2016-09-08
申请号：US14635168
申请日：2015-03-02
发明人： Brandon W. Spangler , Gina Cavallo
CPC分类号： F01D9/065 , F01D5/188 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/64 , F05D2230/642 , F05D2240/12 , F05D2240/126 , F05D2260/221
摘要： An airfoil includes an airfoil body extending from an inner diameter platform to an opposed outer diameter platform along a longitudinal axis. The airfoil body defines a leading edge and a trailing edge and has a cavity defined between the leading edge, the trailing edge, the inner diameter platform and the outer diameter platform. The cavity includes an airfoil protrusion extending inward from an inner surface of the airfoil body. The airfoil includes a baffle body within the cavity extending along a baffle body axis. The baffle body has a baffle protrusion extending along a central protrusion axis at an angle with respect to the baffle body axis. The end of the baffle protrusion abuts an end of the airfoil protrusion. A flow path is defined between the inner surface of the airfoil body and the outer surface of the baffle body.
摘要翻译： 机翼包括从内径平台沿着纵向轴线延伸到相对的外径平台的翼型件主体。 机翼本体限定前缘和后缘，并且具有限定在前缘，后缘，内径平台和外径平台之间的空腔。 空腔包括从翼型体的内表面向内延伸的翼型突起。 翼型件包括沿着挡板主体轴线延伸的腔体内的挡板体。 挡板体具有挡板突出部，该挡板突起沿着中心突出轴线相对于挡板主体轴线成一定角度延伸。 挡板突出部的端部邻接翼型件突出部的一端。 在翼型体的内表面和挡板体的外表面之间限定流动路径。
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公开(公告)号：US10329932B2
公开(公告)日：2019-06-25
申请号：US14635168
申请日：2015-03-02
发明人： Brandon W. Spangler , Gina Cavallo
摘要： An airfoil includes an airfoil body extending from an inner diameter platform to an opposed outer diameter platform along a longitudinal axis. The airfoil body defines a leading edge and a trailing edge and has a cavity defined between the leading edge, the trailing edge, the inner diameter platform and the outer diameter platform. The cavity includes an airfoil protrusion extending inward from an inner surface of the airfoil body. The airfoil includes a baffle body within the cavity extending along a baffle body axis. The baffle body has a baffle protrusion extending along a central protrusion axis at an angle with respect to the baffle body axis. The end of the baffle protrusion abuts an end of the airfoil protrusion. A flow path is defined between the inner surface of the airfoil body and the outer surface of the baffle body.
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公开(公告)号：US10012106B2
公开(公告)日：2018-07-03
申请号：US14613093
申请日：2015-02-03
发明人： Brandon W. Spangler , Gina Cavallo
CPC分类号： F01D25/12 , F01D5/188 , F01D5/189 , F01D9/02 , F01D9/041 , F05D2220/30 , F05D2240/12 , F05D2240/126 , F05D2260/221 , Y02T50/676
摘要： A turbine engine component includes an internal baffle spaced between first and second walls. Each wall may have a plurality of cooling holes in fluid communication with respective upstream and downstream cooling paths defined between the baffle and the respective walls. Cooling air first flows through an upstream end portion of the upstream cooling path, then through a downstream end portion where the air enters a bleed aperture in the baffle. From the bleed aperture, a portion of or all of the cooling air may enter an internal cavity defined by the baffle and, from there, flows through at least one hole that may be a plurality of impingement holes in the baffle, and into the downstream cooling passage where the portion or all of the remaining cooling air may exit the component through the cooling holes in the second wall.
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公开(公告)号：US20180245472A1
公开(公告)日：2018-08-30
申请号：US15919253
申请日：2018-03-13
发明人： Brandon W. Spangler , Gina Cavallo
CPC分类号： F01D5/187 , F01D5/186 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2240/11 , F05D2240/12 , F05D2240/20 , F05D2250/184 , F05D2250/185 , F05D2250/75 , F05D2260/202 , F05D2260/2212 , F05D2260/22141
摘要： A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a wall that extends about a cooling cavity. The cooling cavity is a dual-fed cavity that is fed from at least two different locations. A rib separates the cooling cavity into a first portion and a second portion that is fluidly isolated from the first portion. The component is an airfoil. The first portion is fed with a first cooling fluid from a first coolant source, and the second portion is fed with a second, different cooling fluid from a second coolant source. The first and second coolant sources are separate and distinct from the component.
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公开(公告)号：US10060445B2
公开(公告)日：2018-08-28
申请号：US14924210
申请日：2015-10-27
发明人： Brandon W. Spangler , Gina Cavallo
IPC分类号： F04D29/58 , F23R3/02 , F01D25/12 , F23R3/04 , F02C7/18 , F04D29/16 , F04D29/52 , F04D29/54 , F04D29/64 , F23R3/00 , F23R3/06 , F01D5/18 , F01D9/06
CPC分类号： F04D29/582 , F01D5/186 , F01D9/065 , F01D25/12 , F02C7/18 , F04D29/164 , F04D29/526 , F04D29/542 , F04D29/644 , F05D2220/32 , F05D2230/10 , F05D2240/11 , F05D2240/12 , F05D2240/15 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/672 , Y02T50/675 , Y02T50/676
摘要： A surface structure having a filmhole pattern is disclosed. The filmhole pattern may be an offset herringbone pattern. For instance, the surface structure may have rows of filmholes arranged in filmrows, each filmrow divided into groups of filmholes. A first group may be oriented to direct cooling air generally outward over a surface of the surface structure and a second group may be oriented to direct cooling air generally inward over a surface of the surface structure. Between the first group and the second group of filmholes in each filmrow, a transition region exists. The adjacent filmrows are arranged to enhance the effectiveness of the convective cooling proximate to the transition regions by causing each filmrow to direct cooling air over the transition region of an adjacent filmrow.
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