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公开(公告)号：EP3112614A1
公开(公告)日：2017-01-04
申请号：EP16175816.4
申请日：2016-06-22
CPC分类号： F01D25/243 , F01D21/003 , F01D25/26 , F01D25/285 , F02K1/80 , F05D2220/32 , F05D2230/60 , F05D2230/64 , F05D2250/281 , F05D2260/30 , Y02T50/671
摘要： Aspects of the disclosure are directed to coupling cases associated with an engine of an aircraft. A first case 202; 402 includes a first plurality of threads 212. A second case 204 includes a second plurality of threads 214. A coupler 206, 406 includes a third plurality of threads 242 and a fourth plurality of threads 244. An interface 232a, 232b is configured to align the first case 202; 402 and the second case 204; 404 before the first plurality of threads 212 engage the third plurality of threads 242 or the second plurality of threads 214 engage the fourth plurality of threads 244.
摘要翻译： 本公开的方面涉及与飞行器的发动机相关联的联接情况。 第一例202; 402包括第一多个线程212.第二壳体204包括第二多个线程214.耦合器206,406包括第三多个线程242和第四多个线程244.接口232a，232b被配置为对准 第一例202; 402和第二壳体204; 在第一多个螺纹212接合第三多个螺纹242之前，第二多个螺纹214接合第四多个螺纹244。
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公开(公告)号：EP3112614B1
公开(公告)日：2020-01-15
申请号：EP16175816.4
申请日：2016-06-22
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公开(公告)号：EP3091200B1
公开(公告)日：2018-06-13
申请号：EP16165137.7
申请日：2016-04-13
CPC分类号： F01D25/243 , F01D25/24 , F02K1/80 , F05D2250/25 , F05D2250/281 , F05D2260/30 , F16B7/06 , F16B33/004 , F16B41/002
摘要： Aspects of the disclosure are directed to a first case 202 including a first plurality of threads 212, a second case 204 including a second plurality of threads 214, an interface 232 configured to provide for at least one of anti-rotation or alignment with respect to the first case 202 and the second case 204, and a nut 206 including a third plurality of threads 242 configured to engage with the first plurality of threads 212 and a fourth plurality of threads 244 configured to engage with the second plurality of threads 214.
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公开(公告)号：EP3091200A1
公开(公告)日：2016-11-09
申请号：EP16165137.7
申请日：2016-04-13
CPC分类号： F01D25/243 , F01D25/24 , F02K1/80 , F05D2250/25 , F05D2250/281 , F05D2260/30 , F16B7/06 , F16B33/004 , F16B41/002
摘要： Aspects of the disclosure are directed to a first case 202 including a first plurality of threads 212, a second case 204 including a second plurality of threads 214, an interface 232 configured to provide for at least one of anti-rotation or alignment with respect to the first case 202 and the second case 204, and a nut 206 including a third plurality of threads 242 configured to engage with the first plurality of threads 212 and a fourth plurality of threads 244 configured to engage with the second plurality of threads 214.
摘要翻译： 本公开的方面涉及包括第一多个螺纹212的第一壳体202，包括第二多个螺纹214的第二壳体204，被配置为提供至少一个防旋转或相对于 第一壳体202和第二壳体204以及包括构造成与第一多个螺纹212接合的第三多个螺纹242的螺母206和被构造成与第二多个螺纹214啮合的第四多个螺纹244。
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公开(公告)号：EP2938863A1
公开(公告)日：2015-11-04
申请号：EP13868006.1
申请日：2013-12-17
CPC分类号： F01D9/041 , F01D25/145 , F01D25/162 , F01D25/24 , F01D25/246 , F01D25/28 , F01D25/30 , F05D2220/32 , F05D2240/15 , F05D2260/231 , F05D2260/30 , F05D2260/31
摘要： A turbine exhaust case comprises a frame, a fairing, a heat shield and a mechanical linkage. The frame comprises an outer ring, an inner ring, and a plurality of struts joining the outer ring and the inner ring. The fairing comprising a ring-strut-ring structure disposed within the frame. The heat shield is disposed between the frame and the fairing. The mechanical linkage couples the heat shield to the fairing. In one embodiment, the heat shield comprises a multi-piece heat shield that inhibits heat transfer between the frame and the fairing. In various embodiments, the mechanical linkage comprises a slip joint or a fixed joint for coupling the heat shield to the fairing.
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公开(公告)号：EP2938845A1
公开(公告)日：2015-11-04
申请号：EP13868402.2
申请日：2013-12-19
CPC分类号： F01D25/145 , F01D9/02 , F01D9/041 , F01D9/065 , F01D25/005 , F01D25/12 , F01D25/125 , F01D25/162 , F01D25/24 , F01D25/30 , F05D2220/32 , F05D2240/15 , F05D2250/185 , F05D2260/202 , F05D2260/231 , Y02T50/673 , Y02T50/675
摘要： A turbine exhaust case (28) for a gas turbine engine (10) comprises a frame (100), a vane fairing (108), a heat shield (124, 126, 128), and a serpentine cooling path. The frame has an outer ring (102) and an inner ring (104) connected by a hollow strut (106) with a radial service line passage (132). The vane fairing is disposed between the inner ring and the outer ring to define a core airflow path. The heat shield is disposed between the vane fairing and the frame. The serpentine cooling flow path passes through and around the outer ring, the inner ring, and the plurality of struts
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