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公开(公告)号：US10287899B2
公开(公告)日：2019-05-14
申请号：US15028777
申请日：2014-10-10
发明人： James A. Dierberger
IPC分类号： F01D5/28 , F01D5/30 , C23C4/06 , C23C30/00 , C23C4/11 , C23C4/129 , C23C4/134 , C04B41/00 , C04B41/45 , C04B41/50 , C04B41/87 , C23C4/10 , C23C14/06 , C23C14/08 , C23C14/30 , C23C16/32 , C23C16/34 , C23C16/40
摘要： A component assembly includes a support structure, a ceramic substrate mounted to the support, and a foam-like coating adhered to one of the support structure and the ceramic substrate. The foam-like coating engages the other of the support structure and the ceramic substrate.
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公开(公告)号：US20160281515A1
公开(公告)日：2016-09-29
申请号：US15035249
申请日：2014-11-03
发明人： James A. Dierberger
摘要： A rotor of a turbine engine includes a mounting slot for receiving a blade. The example blade is formed from a ceramic material and is received within the mounting slot. An intumescent material is disposed within the mounting slot between the blade and an inner surface of the mounting slot and expanded by the application of heat for securing the blade within the mounting slot.
摘要翻译： 涡轮发动机的转子包括用于接收叶片的安装槽。 示例性刀片由陶瓷材料形成并被容纳在安装槽内。 膨胀材料设置在叶片与安装槽的内表面之间的安装槽内，并通过施加热而膨胀，以将叶片固定在安装槽内。
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公开(公告)号：US10914470B2
公开(公告)日：2021-02-09
申请号：US14775446
申请日：2014-03-13
发明人： James A. Dierberger
摘要： A liner panel for a combustor of a gas turbine engine includes a nominal wall thickness and a thickened wall thickness in the region of a hot spot.
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公开(公告)号：US09958160B2
公开(公告)日：2018-05-01
申请号：US14765222
申请日：2014-02-04
发明人： James A. Dierberger
CPC分类号： F23R3/06 , F01D25/12 , F01D25/30 , F05D2260/202 , F05D2260/4031 , F23R3/002 , F23R3/005 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/676
摘要： A component within a gas turbine engine includes a surface with one or more upstream-directed cooling film holes therethrough.
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5.发明申请公开(公告)号：US20150369487A1
公开(公告)日：2015-12-24
申请号：US14765222
申请日：2014-02-04
发明人： James A. Dierberger
CPC分类号： F23R3/06 , F01D25/12 , F01D25/30 , F05D2260/202 , F05D2260/4031 , F23R3/002 , F23R3/005 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/676
摘要： A component within a gas turbine engine includes a surface with one or more upstream-directed cooling film holes therethrough.
摘要翻译： 燃气涡轮发动机内的部件包括具有一个或多个上游冷却膜孔的表面。
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公开(公告)号：US09988911B2
公开(公告)日：2018-06-05
申请号：US14767498
申请日：2014-02-05
发明人： James A. Dierberger
IPC分类号： F02C7/12 , F01D5/18 , F01D9/04 , F01D11/08 , F01D25/12 , F01D25/28 , F01D25/30 , F23R3/06 , F01D9/06 , F23R3/00
CPC分类号： F01D5/186 , F01D9/041 , F01D9/065 , F01D11/08 , F01D25/12 , F01D25/28 , F01D25/30 , F05D2220/32 , F05D2230/13 , F05D2230/14 , F05D2240/11 , F05D2240/80 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/03042 , Y02T50/676
摘要： A gas turbine engine component includes a wall that provides exterior and interior surfaces. The interior surface faces an internal cooling passage of the gas turbine engine component. An aperture extends through the wall and interconnects the interior and exterior surfaces to one another and is configured to provide a cooling fluid from the cooling passage to the exterior surface. The aperture has first and second outlet holes overlapping one another at an intersection to provide opposing sharp corners at the intersection.
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公开(公告)号：US20160251972A1
公开(公告)日：2016-09-01
申请号：US15028777
申请日：2014-10-10
发明人： James A. Dierberger
IPC分类号： F01D5/30 , C23C16/32 , C23C16/34 , C23C14/08 , C23C14/06 , C23C4/11 , C23C4/10 , C23C4/129 , C23C4/134 , C23C14/30 , F01D5/28 , C04B41/00 , C04B41/50 , C04B41/45 , C04B41/87 , C23C16/40
CPC分类号： F01D5/3007 , C04B41/009 , C04B41/4523 , C04B41/4527 , C04B41/4529 , C04B41/4531 , C04B41/4582 , C04B41/5025 , C04B41/87 , C23C4/06 , C23C4/10 , C23C4/11 , C23C4/129 , C23C4/134 , C23C14/0635 , C23C14/0652 , C23C14/083 , C23C14/30 , C23C16/325 , C23C16/345 , C23C16/405 , C23C30/00 , F01D5/284 , F01D5/288 , F01D5/3092 , F05D2220/32 , F05D2230/311 , F05D2230/312 , F05D2230/313 , F05D2230/314 , F05D2240/24 , F05D2300/20 , F05D2300/514 , F05D2300/6033 , F05D2300/612
摘要： A component assembly includes a support structure, a ceramic substrate mounted to the support, and a foam-like coating adhered to one of the support structure and the ceramic substrate. The foam-like coating engages the other of the support structure and the ceramic substrate.
摘要翻译： 组件组件包括支撑结构，安装到支撑件上的陶瓷衬底和粘附到支撑结构和陶瓷衬底中的一个的泡沫状涂层。 泡沫状涂层与支撑结构和陶瓷基体中的另一个接合。
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公开(公告)号：US20160040879A1
公开(公告)日：2016-02-11
申请号：US14775446
申请日：2014-03-13
发明人： James A. Dierberger
CPC分类号： F23R3/002 , F02C7/18 , F23R3/005 , F23R3/50 , F23R2900/00005 , F23R2900/03042 , Y02T50/675
摘要： A liner panel for a combustor of a gas turbine engine includes a nominal wall thickness and a thickened wall thickness in the region of a hot spot.
摘要翻译： 用于燃气涡轮发动机的燃烧器的衬板包括在热点区域中的标称壁厚和增厚壁厚。
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公开(公告)号：US20160003054A1
公开(公告)日：2016-01-07
申请号：US14767498
申请日：2014-02-05
发明人： James A. Dierberger
CPC分类号： F01D5/186 , F01D9/041 , F01D9/065 , F01D11/08 , F01D25/12 , F01D25/28 , F01D25/30 , F05D2220/32 , F05D2230/13 , F05D2230/14 , F05D2240/11 , F05D2240/80 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/03042 , Y02T50/676
摘要： A gas turbine engine component includes a wall that provides exterior and interior surfaces. The interior surface faces an internal cooling passage of the gas turbine engine component. An aperture extends through the wall and interconnects the interior and exterior surfaces to one another and is configured to provide a cooling fluid from the cooling passage to the exterior surface. The aperture has first and second outlet holes overlapping one another at an intersection to provide opposing sharp corners at the intersection.
摘要翻译： 燃气涡轮发动机部件包括提供外表面和内表面的壁。 内表面面对燃气涡轮发动机部件的内部冷却通道。 孔径延伸穿过壁并将内表面和外表面彼此互连，并且构造成提供从冷却通道到外表面的冷却流体。 该孔具有在交叉点处彼此重叠的第一和第二出口孔，以在交叉点处提供相对的尖角。
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