-
公开(公告)号：EP4325027A3
公开(公告)日：2024-04-24
申请号：EP24151047.8
申请日：2021-04-27
申请人： RTX Corporation
发明人： MARTIN, Thomas J. , HOLOWCZAK, John E. , KENNEDY, Matthew B. , CROTEAU, Paul F. , ATTRIDGE, Paul
CPC分类号： F01D5/284 , F01D5/282 , F01D5/147 , F01D9/02 , F05D2300/60320130101 , F05D2300/603320130101 , F05D2230/9020130101 , F01D5/288 , F01D9/041 , Y02T50/60
摘要： An airfoil (58) includes an airfoil section (60) that has an airfoil wall (62) that surrounds a cavity (63). The airfoil wall (62) includes an exterior monolithic ceramic shell (64) and an interior CMC liner (66) that has CMC plies (66a, 66b, 66c, 66d). An outermost ply (66d) of the CMC plies (66a, 66b, 66c, 66d) forms tabs (68) that are raised from an underlying ply (66c) so as to define a slot (70). The exterior monolithic ceramic shell (64) includes an underlapping shell piece (76, 78) and an overlapping shell piece (72, 74). The underlapping shell piece (76, 78) has a portion disposed in the slot (70) and bonded with the tabs (68). The overlapping shell piece (72, 74) extends over the tabs (68) and is bonded to the tabs (68). There are channels (82) bounded by adjacent ones of the tabs (68), the underlapping shell piece (76, 78), and the overlapping shell piece (72, 74). Channel orifices (82a) through the CMC liner (66) connect the cavity (63) and the channels (82).
-
公开(公告)号：EP4321731A3
公开(公告)日：2024-04-24
申请号：EP23220151.7
申请日：2021-01-11
申请人： RTX Corporation
CPC分类号： F01D5/147 , F05D2230/21120130101 , F01D5/288 , F05D2240/8020130101 , F05D2240/12120130101 , F05D2240/12220130101 , F05D2240/12520130101 , F05D2240/30320130101 , F05D2240/30420130101 , F05D2240/30720130101 , F05D2300/17320130101 , F05D2230/2220130101 , Y02T50/60
摘要： A blade or vane has: an airfoil having an inner diameter (ID) end and an outer diameter (OD) end and having a suction side and a pressure side and a leading edge and a trailing edge; and an inner platform and/or attachment root at the ID end and/or an outer platform at the OD end. At least one of the inner platform, root, and/or outer platform comprises one or more pieces of a first alloy. One or more pieces of a second alloy form a leading edge section of the airfoil. One or more pieces of a third alloy form a trailing edge section of the airfoil. One or more pieces of a fourth alloy form a spar of the airfoil between the leading edge section and trailing edge section and extending into said at least one of the inner platform, root, and/or outer platform.
-
公开(公告)号：EP4310298A3
公开(公告)日：2024-04-24
申请号：EP23216013.5
申请日：2020-09-17
申请人： RTX Corporation
发明人： FARRIS, John R.
IPC分类号： F01D5/28
CPC分类号： F05D2300/603320130101 , F01D5/282 , C04B35/80 , C04B2235/524420130101 , C04B35/565 , C04B2235/525620130101 , B32B5/024 , B32B2260/0420130101 , B32B2603/0020130101 , B32B2262/10520130101 , B32B2260/02320130101 , B32B5/26 , F01D21/003 , F01D5/284 , F05D2260/8020130101 , F05D2260/8320130101 , F05D2250/2820130101 , F05D2270/80420130101 , Y02T50/60
摘要： An example method for manufacturing a component 300, 400 of a gas turbine engine 20 is provide. The method includes forming a tow 201, 202, 203 of filaments of a fiber material. The method further includes weaving the tow together with other tows to form a sheet 200 of the fiber material. The method further includes forming the component from the sheet of fiber material, the component comprising a designated surface area 213, 412 having a unique pattern 310, 410 created from properties of the fiber material.
-
公开(公告)号：EP4115053B1
公开(公告)日：2024-04-24
申请号：EP21714645.5
申请日：2021-03-03
CPC分类号： F05D2220/3620130101 , F01D5/282 , F05D2300/603420130101 , F04D29/023 , F04D29/324 , B29C70/24 , B29D99/0025 , D03D25/005 , D10B2505/0220130101 , B29L2031/08220130101 , F01D5/147 , Y02T50/60
-
75.发明授权
-
公开(公告)号：EP3613977B1
公开(公告)日：2024-04-24
申请号：EP19192489.3
申请日：2019-08-20
IPC分类号： F02K5/00
CPC分类号： F05D2230/8020130101 , F05D2230/7220130101 , F05D2230/6020130101 , F05D2230/7020130101 , F05D2220/76620130101 , F05D2220/7620130101 , F01D15/10 , F01D25/285 , F02K5/00 , F02C6/14 , F02C7/32 , B64D27/02 , B64F5/40 , Y02T50/60 , B64D27/026
-
公开(公告)号：EP4353605A2
公开(公告)日：2024-04-17
申请号：EP24159903.4
申请日：2021-02-19
发明人： Vermeiren, Sébastien
IPC分类号： B64U50/19
摘要： An engine for an aircraft is presented comprising a rotor, an electric motor actuating the rotation of the rotor and an ECU controlling the electric motor, wherein the rotation of the rotor provides a main flow of air causing the thrust of the engine and wherein the ECU is located within the volume defined by the main flow. The engine comprises one or more hollow pylons that house at least part of or all the cabling of the ECU. The one or more hollow pylons connect the hub of the engine with the fan casing area of the engine.
-
-
-
公开(公告)号：EP4059846B1
公开(公告)日：2024-04-17
申请号：EP22157192.0
申请日：2022-02-17
CPC分类号： B64D33/00 , B64D27/24 , F02C7/32 , F05D2220/76620130101 , F05D2260/3120130101 , F02K1/04 , Y02T50/60 , B64D27/026
-
-
-
-
-
-
-
-
-
搜索结果
445 条记录 (耗时 0.019 秒)
