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1.发明公开公开(公告)号：US20230272720A1
公开(公告)日：2023-08-31
申请号：US17682674
申请日：2022-02-28
CPC分类号： F01D5/282 , F01D5/147 , F05D2300/6033 , F05D2230/50 , C23C16/045
摘要： Disclosed herein is a ceramic matrix composite airfoil comprising a triple bifurcated ply that defines a suction side, an outer platform, a pressure side and an inner platform of the airfoil, wherein the triple bifurcated ply comprises at least one ply that comprises a consolidated region, wherein the consolidated region is split into two bifurcated regions in three locations in three different directions.
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公开(公告)号：US11674540B2
公开(公告)日：2023-06-13
申请号：US16407438
申请日：2019-05-09
申请人： ROHR, INC.
CPC分类号： F16B17/00 , F01D25/28 , F02K1/56 , F02K1/74 , F16M13/02 , F05D2230/50 , F05D2260/30 , F05D2300/603 , F05D2300/6034 , Y02T50/60
摘要： A thrust reverser for a nacelle may comprise a composite track beam and a composite lug. The composite lug may be inserted through a through-hole in the composite track beam. Continuous fibers in the composite lug may provide strength in the in-plane direction.
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公开(公告)号：US20180272470A1
公开(公告)日：2018-09-27
申请号：US15762694
申请日：2016-09-01
发明人： Ralf Bode , Dieter Naß
IPC分类号： B23K26/342 , F01D25/00 , F01D25/24
CPC分类号： B23K26/342 , B23K5/18 , B23K9/048 , B23K10/027 , B23K26/34 , B23K26/38 , B23K2101/001 , B23K2101/04 , B23K2101/06 , B23P15/008 , F01D25/007 , F01D25/243 , F05D2220/40 , F05D2230/50 , F05D2230/90 , F05D2260/95
摘要： A method for manufacturing a housing of a turbomachine, in particular a housing of a radial turbo compressor. The method includes the following steps: a) providing a hollow body that is closed in a circumferential direction and extends along an axis; b) coating the inner side of the hollow body with a corrosion-resistant layer that is more resistant to corrosion than the material of the hollow body; c) dividing the hollow body into two half-shells along the axis in a separation joint plane; d) assembling the housing by joining both half-shells and fastening both half-shells in the region of the separation joints, which were created by separation, by means of detachable fastening elements.
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公开(公告)号：US20180238755A1
公开(公告)日：2018-08-23
申请号：US15437515
申请日：2017-02-21
CPC分类号： G01L5/0071 , B28B1/001 , B28B17/009 , B33Y10/00 , B33Y50/02 , B33Y80/00 , F01D5/02 , F01D5/28 , F01D9/023 , F01D17/04 , F01D25/24 , F04D29/324 , F04D29/522 , F04D29/542 , F04D29/545 , F05D2220/31 , F05D2220/32 , F05D2230/30 , F05D2230/50 , F05D2300/175 , F05D2300/177 , G01B11/16 , G01L1/247 , G01M5/0016 , G01M15/14
摘要： A method of making a component includes forming the component, the component including an internal volume including a first material and an outer surface. The method further includes directly depositing a plurality of fiducial markers on the outer surface, the fiducial markers including a second material that is compatible with the first material. The plurality of fiducial markers form a passive strain indicator, the passive strain indicator including an analysis region, a locator region, and a serial region. At least one of the plurality of fiducial markers is deposited in each of the analysis region, the locator region, and the serial region.
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公开(公告)号：US20180195414A1
公开(公告)日：2018-07-12
申请号：US15742167
申请日：2016-05-19
发明人： Rüdiger Backasch , Mario Rolle , Paramdeep Singh
CPC分类号： F01D25/243 , F01D25/28 , F01D25/30 , F05D2220/31 , F05D2230/50
摘要： An exhaust-steam casing for a turbine, the exhaust-steam casing being designed to discharge the exhaust steam of the turbine in a radial direction with respect to a longitudinal axis of a rotor shaft of the turbine and having an upper exhaust-steam casing part and at least one side exhaust-steam casing part. The upper exhaust-steam casing part and/or the side exhaust-steam casing part have a lower exhaust-steam casing part connection surface for connecting the exhaust-steam casing to a lower exhaust-steam casing part. A turbine frame, a turbine casing and an assembly system for a turbine has an exhaust-steam casing.
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公开(公告)号：US20180128205A1
公开(公告)日：2018-05-10
申请号：US15346291
申请日：2016-11-08
申请人： ROHR, INC.
CPC分类号： F02K1/56 , F01D25/28 , F02K1/74 , F05D2230/50 , F05D2260/30 , F05D2300/603 , F05D2300/6034 , F16B17/00 , Y02T50/672
摘要： A thrust reverser for a nacelle may comprise a composite track beam and a composite lug. The composite lug may be inserted through a through-hole in the composite track beam. Continuous fibers in the composite lug may provide strength in the in-plane direction.
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公开(公告)号：US20180126687A1
公开(公告)日：2018-05-10
申请号：US15804179
申请日：2017-11-06
申请人： Ratier-Figeac SAS
发明人： Pascal AMAT , Stéphane GRIMAL
CPC分类号： B32B3/12 , B29C70/16 , B29C70/865 , B29C70/887 , B29D99/0003 , B29D99/0025 , B29K2063/00 , B29K2101/10 , B29K2101/12 , B29K2307/04 , B29K2309/08 , B29L2031/082 , B32B5/02 , B32B5/18 , B32B37/14 , B32B2305/72 , B32B2603/00 , B64C11/26 , F01D5/282 , F04D29/388 , F05D2230/50
摘要： A method of manufacturing a composite component comprises forming a core, surrounding the circumference of the core with a first layer of fabric, applying a second layer of fabric having a different coefficient of thermal expansion from the first layer such that the second layer extends around at least a portion of the circumference of the core and curing the component such that the second layer imparts a compressive or tensile force on the core.
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公开(公告)号：US20180119570A1
公开(公告)日：2018-05-03
申请号：US15342185
申请日：2016-11-03
CPC分类号： F01D25/12 , F01D5/187 , F01D11/08 , F02C3/04 , F05D2230/22 , F05D2230/50 , F05D2240/11 , F05D2240/128 , F05D2240/30 , F05D2240/81 , F05D2250/71 , F05D2260/204 , F05D2260/2214
摘要： A cooled structure of a gas turbine engine has a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and is arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and is arranged along the second side portion. The first and second set of cooling air micro-channels have turning portions positioned adjacent each other and interwoven exhaust ends originating from each opposing side micro-channel. Each interwoven exhaust end extends around the opposing turning portion and is configured to exhaust cooling air from a plurality of exhaust ports positioned generally radially outward from the turning portions.
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公开(公告)号：US09933164B2
公开(公告)日：2018-04-03
申请号：US15120015
申请日：2015-01-27
IPC分类号： F23R3/52 , F23R3/58 , F02C7/20 , F23R3/50 , F23R3/54 , F23R3/28 , F23R3/42 , F23R3/48 , F23C5/02 , F23R3/46 , F23R3/56 , F23R3/60 , F23D11/10 , F23R3/00
CPC分类号： F23R3/52 , F02C7/20 , F05D2230/50 , F05D2230/51 , F05D2230/64 , F05D2230/642 , F05D2240/35 , F05D2240/90 , F05D2260/30 , F23C5/02 , F23D11/103 , F23R3/002 , F23R3/007 , F23R3/28 , F23R3/283 , F23R3/42 , F23R3/425 , F23R3/46 , F23R3/48 , F23R3/50 , F23R3/54 , F23R3/56 , F23R3/58 , F23R3/60 , F23R2900/00005 , F23R2900/00017 , F23R2900/00018 , F23R2900/00019
摘要： An annular combustion chamber (10) for a turbomachine (100), the combustion chamber presenting an axial direction (X), a radial direction, and an azimuth direction, and comprising a first annular wall (12) and a second annular wall (14), each wall delimiting at least a portion of the volume of the annular combustion chamber (10), the first and second walls (12, 14) presenting complementary fitting elements (12d, 14d), the first wall (12) presenting at least one first through hole (12f), while the second wall (14) presents at least one second through hole (14f), the combustion chamber (10) also having at least one pin (18) engaged in a pair of holes comprising a first hole (12f) and a second hole (14f), said pin (18) locking the fitting of the first and second walls (12, 14).
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公开(公告)号：US20180089361A1
公开(公告)日：2018-03-29
申请号：US15280118
申请日：2016-09-29
发明人： Tao Guo , Michael Ernest Boisclair , Joseph Anthony Cotroneo , Douglas Carl Hofer , Amir Mujezinovic , Vsevolod Yuriyevich Ostrovskiy
CPC分类号： G06F17/5086 , F01D5/141 , F01D5/16 , F01D5/225 , F01D9/02 , F04D29/324 , F04D29/542 , F05D2220/31 , F05D2220/32 , F05D2230/50 , F05D2240/12 , F05D2240/125 , F05D2240/30 , F05D2240/307 , F05D2250/29 , F05D2260/96
摘要： The present disclosure is directed to a method for scaling an airfoil for placement in a turbomachine. The method disclosed herein includes radially scaling a master airfoil to form a scaled airfoil. The method may also include tuning the scaled airfoil. For example, tuning the scaled airfoil may include axially scaling. The scaled airfoil generally has similar characteristics to the master airfoil.
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