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公开(公告)号：EP2938827B1
公开(公告)日：2018-11-14
申请号：EP13869611.7
申请日：2013-05-15
CPC分类号： F23R3/002 , B22F3/1055 , B23P15/26 , B33Y10/00 , B33Y70/00 , B33Y80/00 , F01D5/147 , F01D5/18 , F01D5/183 , F01D5/184 , F01D5/186 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/08 , F01D25/12 , F01D25/24 , F02C7/18 , F05D2250/185 , F05D2260/204 , F23R2900/03043 , Y10T29/49318 , Y10T29/49337 , Y10T29/49343 , Y10T29/49352 , Y10T428/249921
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure. A method for producing a component is also disclosed.
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公开(公告)号：EP3394401A1
公开(公告)日：2018-10-31
申请号：EP16826089.1
申请日：2016-12-12
发明人： BRAULT, Michel, Gilbert, Roland , BORDONI, Nils, Edouard, Romain , CUVILLIER, Romain, Guillaume , KUBIAK, Guillaume, Patrice , NEGRI, Arnaud, Nicolas , NOWAKOWSKI, Nathalie
CPC分类号： F02C7/20 , F01D25/162 , F01D25/24 , F01D25/246 , F01D25/28 , F02K3/06 , F05D2230/642 , F05D2240/90 , F05D2250/41 , Y02T50/671
摘要： The present invention relates to a multiflow turbojet engine comprising: a. an upstream fan (2) driven by a gas generator; b. the gas generator comprising first (3) and second (4) coaxial compressors; c. an intake case (8) forming a mounting for the rotors of the fan (2) and the first compressor (3); d. an inter-compressor case (9) downstream from the intake case (8) and forming a mounting for the rotor of the second compressor (4); and e. attachment means for thrust take-up control rods (95) arranged in the inter-compressor case. The turbojet engine is characterised in that it comprises a structural force shroud (32) connecting the intake case (8) to the inter-compressor case (9), the case (31) of the first compressor being floating.
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公开(公告)号：EP3167164B1
公开(公告)日：2018-10-31
申请号：EP15774541.5
申请日：2015-09-23
CPC分类号： F01D9/023 , B23K26/21 , F01D25/08 , F01D25/12 , F01D25/14 , F01D25/24 , F02K1/82 , F02K1/822 , F05D2230/22 , F05D2230/54 , F05D2250/292 , F05D2260/20 , F05D2260/202 , F05D2260/203 , F23R3/002 , F23R3/005 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： The invention is directed to a turbomachine component (10), particularly a gas turbine engine component, comprising at least one part (2) built in parts from a curved or planar panel (11), particularly a sheet metal, the part (2) comprising a plurality of cooling channels (3) via which a cooling fluid (5), particularly air, is guidable, wherein at least one of the plurality of cooling channels (3) has a continuously tapered section (8). The invention furthermore is directed to a gas turbine engine equipped with such a component and a method of manufacturing.
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公开(公告)号：EP2819921B1
公开(公告)日：2018-10-24
申请号：EP13708203.8
申请日：2013-02-13
申请人： Safran Nacelles
CPC分类号： F01D25/24 , B64D15/04 , B64D33/02 , B64D33/10 , B64D2033/0233 , F02C7/047 , F02C7/12 , F02K3/06 , F05D2240/14 , F05D2260/213 , Y02T50/676
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公开(公告)号：EP3385065A1
公开(公告)日：2018-10-10
申请号：EP18165438.5
申请日：2018-04-03
CPC分类号： B28B23/0006 , B28B17/0009 , B29C70/44 , B29C70/545 , B29K2883/00 , B29L2031/749 , C04B35/71 , C04B2235/602 , C04B2235/94 , F01D25/005 , F01D25/24 , F02C3/04 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2260/40311 , F05D2300/6033
摘要： Various methods and assemblies are provided for producing composite components (90) having formed in features. For example, a method may comprise depositing a composite material (102) on a base tool (100,200,300) (100); bringing a feature forming tool (110,210,310,410,510) (110) into contact with the composite material (102); and processing the composite material (102) with the feature forming tool (110,210,310,410,510) in contact with the composite material (102). The processed composite material (102) forms a green state composite component. The feature forming tool (110,210,310,410,510) (110) comprises a sheet (112) having one or more elements for interacting with one or more elements of the base tool (100,200,300) to form one or more features of the composite component (90). In some embodiments, the method also may comprise sealing (708,1208,1510,1710) a bag (125) around the feature forming tool (110,210,310,410,510) (110) and the composite material (102) after bringing the tool into contact with the composite material (102) and removing (712,912,1212,1514,1714) the bag (125) and the feature forming tool (110,210,310,410,510) from the green state composite component after processing.
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公开(公告)号：EP3354863A3
公开(公告)日：2018-10-10
申请号：EP18152525.4
申请日：2018-01-19
发明人： BINSBERGER, Dale R.
CPC分类号： F01D25/04 , F01D25/24 , F01D25/28 , F05D2240/70 , F05D2240/90 , F05D2260/31 , F05D2260/96 , F05D2300/501 , F05D2300/603 , F16B5/0241 , F16B37/122 , F16B43/001 , Y02T50/672
摘要： The present invention is related to an assembly (46) for a gas turbine engine for providing vibration damping between a component and a mount. This assembly (46) includes a mount (50), a component (48) and a fastener assembly (52) attaching the component (48) to the mount (50). The fastener assembly (52) includes a fastener (68), a bushing (70) and a damper (72). The fastener (68) extends axially along an axis through an aperture in the component (48) and into the mount (50). The bushing (70) extends axially along the axis through the aperture and axially engages the mount (50) and the fastener (68). The damper (72) is configured to damp vibration transmission between the mount (50) and the component (48). The damper (72) is arranged between the mount (50) and the component (48) and between the component (48) and the bushing (70). This assembly improves attachment of composites and metals.
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公开(公告)号：EP2927433B1
公开(公告)日：2018-09-26
申请号：EP15161187.8
申请日：2015-03-26
CPC分类号： F01D11/14 , F01D11/24 , F01D17/00 , F01D25/145 , F01D25/24 , F02C5/12 , F02C7/25 , F05D2220/32 , F05D2260/231
摘要： A gas turbine engine (20) includes a fluid intake (70). A turbine section (28) includes a turbine case (64). A firewall (76) is located upstream of the turbine section (28). A conduit (74) is configured to direct a fluid from the fluid intake (70) to the turbine case (64). A valve (80) is located on a first side of the firewall (76) opposite from the turbine section (28) and is configured to regulate a flow of the fluid through the conduit (74).
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公开(公告)号：EP3376011A1
公开(公告)日：2018-09-19
申请号：EP18157531.7
申请日：2018-02-20
申请人： Rolls-Royce plc
发明人： Pointon, James , Bradbrook, Stephen
CPC分类号： F02C7/36 , F01D25/24 , F02C9/18 , F02K3/06 , F05D2220/3216 , F05D2220/323 , F05D2240/60 , Y02T50/671
摘要： An aircraft gas turbine engine (10) includes a compressor system comprising a low pressure compressor (15) coupled to a low pressure shaft (23), and a high pressure compressor (16) coupled to a high pressure shaft (24). The engine includes an inner core casing (34) provided radially inwardly of compressor blades (42) of the compressor system, and an outer core casing arrangement provided radially outwardly of compressor blades (42) of the compressor system, the inner core casing and outer core casing arrangement defining a core working gas flow path (B) therebetween. The engine also includes a fan (13) coupled to the low pressure shaft (23) via a reduction gearbox (14); the outer core casing arrangement comprising a first outer core casing (48) and a second outer core casing (50) spaced radially outwardly from the first outer core casing (48). At an axial plane (E) of an inlet to the high pressure compressor (16), the second outer core casing (50) has an inner radius at least 1.4 times the inner radius of the first outer core casing (48).
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公开(公告)号：EP3372801A1
公开(公告)日：2018-09-12
申请号：EP16862148.0
申请日：2016-11-02
CPC分类号： F01D25/243 , F01D9/026 , F01D25/24 , F02B39/00 , F05D2220/40 , F05D2230/21 , F05D2230/232 , F05D2250/51
摘要： In a turbine housing (10) that includes a scroll portion (20) constituting a spiral exhaust gas passage (K) between an exhaust inlet side flange (12) constituting an inlet for exhaust gas and an exhaust outlet side flange (13) constituting an outlet for the exhaust gas, the turbine housing (10) discharging the exhaust gas to an exhaust outlet side through a turbine wheel (14) disposed in a central portion (O) of the scroll portion (20), a part of a passage face (k) of the exhaust gas passage (K), in the scroll portion (20), is formed from a scroll member (23) made of a casting.
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公开(公告)号：EP3056765B1
公开(公告)日：2018-09-05
申请号：EP14873062.5
申请日：2014-12-17
CPC分类号： F01D17/145 , F01D5/02 , F01D5/12 , F01D25/24 , F05D2220/31 , F05D2260/57 , F05D2270/58 , F05D2270/62 , F16H25/2204 , F16H57/0497 , F16K31/047
摘要： A linear motion mechanism (27) is provided with: a cylinder rod (312) into which a ball screw (30) can be inserted, said cylinder rod (312) comprising a base end section that is connected to a nut (311) within a piston casing (36) and a tip section (312a) that is exposed on the outside of the piston casing (36); a nut-side grease supply hole (321) that is formed in the nut (311) and that comprises a discharge port (323) that opens toward the outer circumferential surface of the ball screw (30); and a cylinder rod-side grease supply hole (322) that is formed in the cylinder rod (312), that comprises on one end thereof an inlet (324) that opens at a position that is exposed to the outer section of the piston casing (36), and that comprises another end (322b) that is connected to the nut-side grease supply hole (321).
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