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公开(公告)号：EP3309363A2
公开(公告)日：2018-04-18
申请号：EP17196241.8
申请日：2017-10-12
CPC分类号： F01D11/003 , F01D25/12 , F01D25/125 , F05D2220/32 , F05D2240/55 , F05D2260/232 , F05D2300/224 , F16J15/162 , F16J15/3404 , F16J15/342 , F16J15/4476 , Y02T50/675
摘要： Aspects of the disclosure are directed to a sealing system (300) for an engine having an axial centerline, comprising: a stationary carbon segment (224), and a seal plate (318) that rotates when the engine is operated, where the seal plate (318) includes an end face (342) that is opposed to an interface (336) between the carbon segment (224) and the seal plate (318), and where the end face (342) includes at least one groove that conveys a liquid cooling fluid.
摘要翻译： 本公开的多个方面涉及一种用于具有轴向中心线的发动机的密封系统（300），包括：固定碳段（224）和密封板（318），当发动机被操作时该密封板（318）旋转，其中密封板 （318）包括与所述碳段（224）和所述密封板（318）之间的界面（336）相对的端面（342），并且其中所述端面（342）包括至少一个沟槽，所述沟槽传送 液体冷却液。
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公开(公告)号：EP3048343A1
公开(公告)日：2016-07-27
申请号：EP16152097.8
申请日：2016-01-20
摘要： Aspects of the disclosure are directed to a system comprising: a first seal 302 that includes a notch 320 configured to avoid an adjacent seal plate radius edge and a first protrusion 312, and a second seal 301 that is notch-free with respect to an inner diameter sealing face and includes a second protrusion 301, wherein the first protrusion 312 and the second protrusion 312 are configured to at least partially overlap with one another in at least one of an axial direction or a radial direction with respect to an engine centerline 220.
摘要翻译： 本公开的多个方面涉及一种系统，该系统包括：第一密封件302，该第一密封件302包括构造成避开相邻的密封板半径边缘的凹口320和第一突起312以及相对于内部 并且包括第二突起301，其中第一突起312和第二突起312构造成相对于发动机中心线220在轴向方向或径向方向中的至少一个方向上至少部分地彼此重叠。
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公开(公告)号：EP3309363A3
公开(公告)日：2018-05-30
申请号：EP17196241.8
申请日：2017-10-12
CPC分类号： F01D11/003 , F01D25/12 , F01D25/125 , F05D2220/32 , F05D2240/55 , F05D2260/232 , F05D2300/224 , F16J15/162 , F16J15/3404 , F16J15/342 , F16J15/4476 , Y02T50/675
摘要： Aspects of the disclosure are directed to a sealing system (300) for an engine having an axial centerline, comprising: a stationary carbon segment (224), and a seal plate (318) that rotates when the engine is operated, where the seal plate (318) includes an end face (342) that is opposed to an interface (336) between the carbon segment (224) and the seal plate (318), and where the end face (342) includes at least one groove that conveys a liquid cooling fluid.
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公开(公告)号：EP3048343B1
公开(公告)日：2020-09-30
申请号：EP16152097.8
申请日：2016-01-20
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公开(公告)号：EP3232011A1
公开(公告)日：2017-10-18
申请号：EP17166339.6
申请日：2017-04-12
CPC分类号： F01D11/003 , F01D11/04 , F01D25/16 , F01D25/183 , F02C7/28 , F05D2220/32 , F05D2240/50 , F05D2240/53 , F05D2240/60 , F16C33/741 , F16C2360/23 , F16J15/406
摘要： Aspects of the disclosure are directed to a system (300;400;500) associated with an engine (10) of an aircraft, the system (300;400;500) comprising a fluid source (240) that is configured to provide a fluid at a first pressure value, a carbon seal (210), a seal plate (216) that includes at least one lift-off feature (234') that interfaces to the carbon seal (210), and a pressure boosting mechanism configured to obtain the fluid from the fluid source (240), increase the pressure of the fluid to a second pressure value, and provide the fluid at the second pressure value to the at least one lift-off feature (234').
摘要翻译： 本公开的多个方面涉及与飞机的发动机（10）相关联的系统（300; 400; 500），所述系统（300; 400; 500）包括流体源（240），所述流体源构造成提供流体 （210），密封板（216），所述密封板（216）包括与所述碳密封件（210）交界的至少一个剥离特征（234'）;以及增压机构，所述增压机构构造成获得第一压力值下的碳密封件 来自流体源（240）的流体将流体的压力增加到第二压力值，并且将处于第二压力值的流体提供给至少一个剥离特征（234'）。
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