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公开(公告)号：EP2826959B1
公开(公告)日：2018-09-05
申请号：EP14176727.7
申请日：2014-07-11
申请人： MTU Aero Engines AG
发明人： Bayer, Erwin , Heß, Thomas , Hiller, Sven-Jürgen , Geiger, Peter
CPC分类号： F01D25/145 , F01D5/28 , F01D5/284 , F01D9/02 , F01D9/04 , F01D9/041 , F01D9/042 , F01D11/005 , F01D25/005 , F01D25/14 , F01D25/24 , F05D2260/231 , Y02T50/675 , Y10T29/49229
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公开(公告)号：EP2935801B1
公开(公告)日：2018-08-29
申请号：EP13874535.1
申请日：2013-11-22
发明人： HARRIS, Meggan
CPC分类号： F01D11/22 , F01D25/24 , F01D25/246
摘要： A variable outer air seal support system according to an exemplary aspect of the present disclosure includes, among other things, a case having a plurality of slots, and an extension of a variable outer air seal segment. The extension provides at least one extension aperture. A connector pin is configured to move within the slot to move the variable outer air seal segment from a first position to a second position. The variable outer air seal segment overlaps a circumferentially adjacent variable outer air seal segment more in the first position than in the second position.
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公开(公告)号：EP3346095A3
公开(公告)日：2018-08-22
申请号：EP17206058.4
申请日：2017-12-07
发明人： HANSON, Gerhart LaMoyne , LAJEUNESSE, Eugene Vincent , PEZANT, Michael Bryan , SCORZA, Paul Michael , SMITH, Martin Lewis , WIESNER, Gary Edward
IPC分类号： F01D5/28
CPC分类号： C23C4/01 , B05B7/00 , C23C4/04 , C23C4/06 , C23C4/11 , C23C4/126 , C23C4/134 , F01D5/005 , F01D5/18 , F01D5/28 , F01D5/288 , F01D9/02 , F01D9/023 , F01D9/04 , F01D9/041 , F01D25/12 , F01D25/24 , F01D25/243 , F02C7/12 , F05D2220/32 , F05D2230/312 , F05D2230/90 , F05D2240/35 , F05D2260/202 , F05D2260/607 , F05D2300/5023 , F05D2300/611 , F23R3/002 , F23R3/04
摘要： A system (2) according to various embodiments can include: a coating system (10) configured to apply a thermal coating material (12) to a component (14), the component (14) having a plurality of cooling holes (16); an airflow system (20) coupled with the coating system (10), the airflow system (20) configured to force air through the component (14); and a control system (40) coupled with the airflow system (20) and the coating system (10), the control system (40) configured to: detect coating instructions (42) for the coating system (10), the coating instructions (42) instructing (42) the coating system (10) to apply the thermal coating material (12) to a subset (16A, 16B) of the plurality of cooling holes (16); and instruct the airflow system (20) to force air through the subset (16A, 16B) of the plurality of cooling holes (16) during application of the thermal coating material (12) to the component (14) in response to detecting the coating instructions (42).
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公开(公告)号：EP3129607B1
公开(公告)日：2018-08-22
申请号：EP15719071.1
申请日：2015-04-13
CPC分类号： F01D25/243 , F01D25/24 , F02C7/20 , F05D2220/30 , F05D2260/30 , F05D2300/5021 , Y02T50/672
摘要： A fairing assembly is provided which is located between a frame hub and an engine casing. The assembly provides for use of a metallic structure in combination with a light weight low alpha material in order to improve engine efficiency and performance. Relative growth between the dissimilar materials is compensated for by a flexible bracket which provides biasing force on one of the assembly components in a cold engine condition as well as allowing for growth at the high temperature operating conditions of the engine.
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公开(公告)号：EP3350420A1
公开(公告)日：2018-07-25
申请号：EP16785191.4
申请日：2016-09-15
CPC分类号： F01D25/285 , B64F5/50 , B66C1/107 , F01D25/24 , F05D2220/32 , F05D2230/60 , F05D2240/14 , F05D2240/90 , F05D2260/31
摘要： The invention relates to the field of supporting interfaces, and particularly a supporting interface (30a, 30b) of this kind for an engine crankcase (90) and including a coupling part (50), a first plurality of bolts (80) and a plurality of pins (70). The coupling part (50) includes an outer surface (52) having a cavity (42) capable of receiving a support arm (20a, 20b), an inner surface (51) which can be mounted on an outer surface (93) of the engine crankcase (90), and a first plurality of openings (53) between the outer surface (52) and the inner surface (51) of the coupling part (50). The bolts (80) each include a threaded rod (82) received in one opening (53) of the first plurality of openings (53), and a head (81) capable of bearing on the outer surface (52) of the coupling part (50). Each pin (70) includes a threaded opening (71) in which the threaded rod (82) of one of the bolts (80) of the first plurality of bolts (80) is inserted through a first end of the pin (70), and a second widened end capable of bearing on an inner surface (92) of the engine crankcase (90). The invention also relates to a method for mounting such a supporting interface.
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公开(公告)号：EP3348803A1
公开(公告)日：2018-07-18
申请号：EP17210986.0
申请日：2014-03-12
发明人： WANG, Cheng-Zhang , GLAHN, Jorn A. , CLOUD, David F. , MUNSELL, Peter M. , CRAWLEY, Clifton J., Jr. , NEWMAN, Robert , STEARNS, Michelle Diana
IPC分类号： F01D25/24 , F01D25/12 , F02C7/12 , F04D29/52 , F04D29/58 , F01D9/04 , F02C7/18 , F01D9/06 , F01D25/16
CPC分类号： F01D25/24 , F01D9/041 , F01D9/065 , F01D25/162 , F02C7/18 , F05D2240/14 , F05D2260/14 , F05D2260/20 , F05D2260/2212 , F05D2260/97 , Y02T50/676
摘要： A frame assembly for a turbine engine, the frame assembly comprising: a plurality of vane struts extending radially outward relative to an axis; an outer cavity (62) which includes an opening for communicating cooling air to a turbine section of the turbine engine; and a transfer tube (68) within the outer cavity configured and adapted to receive cooling air, the transfer tube including a bend (80) relative to the engine axis to impart circumferential velocity into cooling air within the outer cavity for maintaining a desired temperature of the cooling air within the outer cavity.
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公开(公告)号：EP3348798A1
公开(公告)日：2018-07-18
申请号：EP17206060.0
申请日：2017-12-07
CPC分类号： F01D1/16 , F01D1/023 , F01D1/04 , F01D17/105 , F01D17/18 , F01D25/24 , F05D2220/31 , F05D2220/76
摘要： A steam turbine system (200, 300, 400, 502), including a plurality of blade stages (202, 306, 404, 506) arranged axially along a first shaft (204), an impulse stage (212, 304, 408, 510) configured upstream of the plurality of blade stages (202, 306, 404, 506), the impulse stage (212, 304, 408, 510) having an impulse wheel (214) and a casing (100, 216), the casing (100, 216) including a plurality of inlet sections (102, 104, 106, 108) with each of the plurality of inlet sections (102, 104, 106, 108) having a corresponding nozzle group (110, 112, 114, 116) and operatively connected to a corresponding control valve (120, 122, 124, 126,) controlling a first steam flow through the corresponding nozzle group (110, 112, 114, 116), a first inlet (132, 134, 136, 138, 232) configured to provide the first steam flow through the impulse stage (212, 304, 408, 510) and the plurality of blade stages (202, 306, 404, 506), and, a second inlet (226, 230) configured to provide a second steam flow to the plurality of blade stages (202, 306, 404, 506) and bypassing the impulse stage (212, 304, 408, 510).
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公开(公告)号：EP3348797A1
公开(公告)日：2018-07-18
申请号：EP17204155.0
申请日：2017-11-28
申请人： The Boeing Company
发明人： JASKLOWSKI, Chris T.
CPC分类号： F01D21/003 , B64D29/00 , F01D17/02 , F01D25/24 , F01D25/28 , F05D2220/323 , F05D2260/83 , H05K7/12
摘要： Systems and methods are provided for a flexible band electrical component mount that includes a flexible band configured to receive one or more electrical components (220A-C). The flexible band is configured to couple to and/or wrap around at least a portion of an aircraft propulsor. The electrical components (220A-C) are configured to output data from the aircraft propulsor and/or data related to operation of the aircraft propulsor. Such flexible bands may be configured to receive a plurality of electrical components (220A-C) and may be configured to wrap around the portion of the aircraft propulsor a plurality of times.
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公开(公告)号：EP3348792A1
公开(公告)日：2018-07-18
申请号：EP17206340.6
申请日：2017-12-11
发明人： Sippel, Aaron , Vetters, Daniel
CPC分类号： F01D11/005 , F01D9/04 , F01D25/24 , F01D25/246 , F05D2240/11 , F05D2240/55 , F05D2300/6033 , F16J15/062 , Y02T50/672
摘要： A gas turbine engine assembly includes adjacent components and a seal assembly. The seal assembly is configured to block gases from passing through the interface of the adjacent components.
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公开(公告)号：EP3347639A1
公开(公告)日：2018-07-18
申请号：EP15760193.1
申请日：2015-09-09
发明人： ERIKSSON, Pontus
CPC分类号： F01D25/265 , F01D25/24 , F02B37/00 , F02C6/12 , F02M35/10144 , F05D2220/40 , F05D2260/30 , F05D2260/39 , F16L23/003 , F16L23/08 , F16L2201/60
摘要： A clamp for connecting a first component end to a second component end is provided. The clamp includes a web extending between a first end and a second end, each end being provided with a connecting device for connecting said web ends to each other so that the clamp encloses the component ends. The clamp further includes an alignment structure, which alignment structure is configured to fit with corresponding engagement structures provided at the first component end and the second component end for circumferentially positioning the clamp relative to the component ends.
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