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公开(公告)号：US10103410B2
公开(公告)日：2018-10-16
申请号：US14719742
申请日：2015-05-22
发明人： Sundeep Kumar , Mohamed Rahmane , Hongbo Cao , Darren Michael Stohr , Raghavendra Rao Adharapurapu , Ravikumar Hanumantha
摘要： A method for joining a metal component to a ceramic component is presented. The method includes disposing a metallic barrier layer on a metallized portion of the ceramic component, and joining the metal component to the metallized portion of the ceramic component through the metallic barrier layer. The metallic barrier layer comprises nickel and a melting point depressant. The metallic barrier layer is disposed by a screen printing process, followed by sintering the layer at a temperature less than about 1000 degrees Celsius. A sealing structure including a joint between a ceramic component and a metal component is also presented.
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公开(公告)号：US11267551B2
公开(公告)日：2022-03-08
申请号：US16685504
申请日：2019-11-15
发明人： Timothy John Sommerer , Nicholas William Rathay , Narendra Digamber Joshi , Douglas Carl Hofer , Hongbo Cao
摘要： A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid, such as liquid metal, to the stagnation point. The liquid metal vaporizes when the leading edge experiences a high heat load, thereby transpiration cooling the leading edge and/or facilitating a magnetohydrodynamic process for generating thrust or electricity.
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公开(公告)号：US20210359338A1
公开(公告)日：2021-11-18
申请号：US16876825
申请日：2020-05-18
发明人： Anil Raj Duggal , Hongyi Zhou , Hongbo Cao , Oltea Puica Siclovan , Kevin Henry Janora , Holly Ann Comanzo
IPC分类号： H01M10/0562 , H01M10/0525
摘要： A porous electrolyte structure for a solid state battery is provided. The porous electrolyte structure has an interconnected ceramic matrix with a network of open pores disposed throughout a thickness of the porous electrolyte structure. The porous electrolyte structure includes a porosity of about 20% by volume to about 80% by volume. A solid state battery cell including the porous electrolyte structure and a method of making the solid state battery cell are also provided.
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公开(公告)号：US20210147060A1
公开(公告)日：2021-05-20
申请号：US16685504
申请日：2019-11-15
发明人： Timothy John Sommerer , Nicholas William Rathay , Narendra Digamber Joshi , Douglas Carl Hofer , Hongbo Cao
摘要： A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid, such as liquid metal, to the stagnation point. The liquid metal vaporizes when the leading edge experiences a high heat load, thereby transpiration cooling the leading edge and/or facilitating a magnetohydrodynamic process for generating thrust or electricity.
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公开(公告)号：US20170101347A1
公开(公告)日：2017-04-13
申请号：US14878192
申请日：2015-10-08
发明人： Julin Wan , Hongbo Cao
CPC分类号： C04B41/0072 , B08B7/04 , C04B41/009 , C04B41/52 , C04B41/53 , C04B41/89 , C04B41/91 , F01D5/282 , F01D5/284 , F01D5/288 , F05D2300/211 , F05D2300/6033 , F05D2300/701 , C04B35/565 , C04B35/806 , C04B35/584 , C04B41/5096 , C04B41/5059 , C04B41/522 , C04B41/5071 , C04B41/5066 , C04B41/5035 , C04B41/5024 , C04B41/459 , C04B2103/0021 , C04B41/5037 , C04B41/5042 , C04B41/4515
摘要： A method for removing a coating from an article includes heating an article to a processing temperature. The article includes a first material in contact with a second material, the first material comprising silicon, and the second material comprising an oxide comprising silicon. The heating is performed in an environment having a partial pressure of oxygen that is less than an equilibrium partial pressure of oxygen for chemical equilibrium between the first material and the second material at the processing temperature.
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