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1.发明公开公开(公告)号：US20240218801A1
公开(公告)日：2024-07-04
申请号：US18555056
申请日：2022-04-12
发明人： Aurélien GAILLARD , Clément Emile André CAZIN , Sébastien Serge Francis CONGRATEL , Clément JARROSSAY , Pascal Cédric TABARIN
CPC分类号： F01D9/041 , F01D5/282 , F01D9/06 , F01D25/24 , F05D2220/323 , F05D2230/10 , F05D2240/128
摘要： A turbine comprising a casing and a nozzle including an outer metallic shroud (9) secured to the casing, an inner metallic shroud, and a plurality of nozzle segments (20) made of CMC forming a crown extending between the outer shroud (9) and the inner shroud, each segment including a strut (6), an inner platform, an outer platform and at least one airfoil having a hollow profile traversed by the strut (6).
For each airfoil (20), the outer platform (26) comprises an axial stop (260) extending in outward radial protrusion from the outer platform (26), and the outer metallic shroud (9) comprises a complementary axial stop (96) extending in inward radial protrusion from the outer metallic shroud (9), the axial stop (260) being upstream and axially bearing against the complementary axial stop (96), and machined with an angle of machining chosen to adjust the orientation of said at least one blade of the segment with respect to the axial direction (DA).-
公开(公告)号：US20240159157A1
公开(公告)日：2024-05-16
申请号：US18158618
申请日：2023-01-24
发明人： Kudum Shinde , Sesha Subramanian , Yashpal Patel
CPC分类号： F01D9/06 , F02C6/08 , F02C9/18 , F05D2220/323 , F05D2240/14 , F05D2260/232 , F05D2260/605 , F05D2260/606
摘要： A gas turbine engine includes a compressor with an inner casing and an outer casing. The inner casing defines a primary flow path for airflow through the compressor, the inner casing and the outer casing define a bleed air cavity therebetween. The inner casing at least partially defines a first bleed air channel between the primary flow path and the first bleed air cavity. The first bleed air channel is defined between a first wall and a second wall, wherein the first wall is upstream from the second wall. The first wall includes a plurality of holes in fluid communication with the primary flow path and fluidly coupled to a suction manifold. The plurality of holes is configured to energize a fluid boundary layer along the first wall.
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公开(公告)号：US11965433B2
公开(公告)日：2024-04-23
申请号：US17997628
申请日：2021-04-28
发明人： Antoine Claude Michel Etienne Danis , Clément Jarrossay , Lucien Henri Jacques Quennehen , Nicolas Paul Tableau , Matthieu Arnaud Gimat
CPC分类号： F01D9/06 , F01D5/284 , F01D25/12 , F05D2220/32 , F05D2220/323 , F05D2240/128 , F05D2260/202 , F05D2300/20
摘要： A turbomachine turbine nozzle extending around a central axis, including at least one radially outer shroud, at least one radially inner shroud, and at least one blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between the radially inner shroud and the radially outer shroud, the blade being hollow and including a cavity opening at a radially inner end and at a radially outer end of the blade, the nozzle including at least one tubular mast arranged in the cavity of the blade and allowing routing the ventilation air passing through the cavity of the blade, the mast including a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with a radial flange for positioning the radially inner shroud.
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公开(公告)号：US11881754B2
公开(公告)日：2024-01-23
申请号：US17780875
申请日：2020-11-24
CPC分类号： H02K5/225 , F01D9/06 , F01D15/10 , H02K7/1823 , H02K15/0006 , F05D2220/323 , F05D2220/76 , F05D2240/10
摘要： Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises: —an elongate body (80a) made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm2, and— an electrical insulation sheath (80b) that surrounds the body, at least one of the longitudinal ends (84a) of the body not being covered by the sheath and comprising a through-hole (86) in which a bolt (88) for fastening and electrically connecting this end is mounted.
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公开(公告)号：US20230417147A1
公开(公告)日：2023-12-28
申请号：US18465487
申请日：2023-09-12
发明人： Apostolos Pavlos Karafillis , Eric Dean Jorgensen , Craig Douglas Young , Jonathan Harry Kerner , Leonardo Ajdelsztajn
CPC分类号： F01D9/06 , B05D1/12 , F01D25/24 , F05D2260/606 , F05D2230/31 , F05D2240/128
摘要： A component for a turbine engine may be formed by spraying particulate with a nozzle toward a substrate. The particulate may be deposited to form one or more annular layers and a reinforcing structure. The component may be a closed loop annular component having a reinforcing structure of specific dimensions enabled by the methods described.
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公开(公告)号：US11828193B2
公开(公告)日：2023-11-28
申请号：US17307997
申请日：2021-05-04
CPC分类号： F01D5/186 , B22C9/10 , B22C9/24 , F01D5/18 , F01D9/02 , F01D9/041 , F01D9/047 , F01D25/12 , F01D5/187 , F01D9/06 , F05D2260/202
摘要： A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.
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公开(公告)号：US20230323785A1
公开(公告)日：2023-10-12
申请号：US17662023
申请日：2022-05-04
发明人： Jeffrey Earl , Freddie Sarhan , Jeremy Liu
CPC分类号： F01D15/10 , F01D17/16 , F01D17/145 , F01D9/06 , F05D2220/7642 , F05D2260/60 , F05D2270/306
摘要： A first turboexpander generator defines a portion of a first conduit flow passage. The first turboexpander generator is configured to decrease a temperature or pressure of a process stream flowing through the first turboexpander generator by generating electrical power from the process stream. A second turboexpander generator defines a portion of a second conduit flow passage. The second turboexpander generator is configured to decrease a temperature or pressure of a process stream flowing through the second turboexpander generator by generating electrical power from the process stream. The first and second conduit flow passages are arranged to carry fluid flow in parallel to one another. The first and the second turboexpander generator are substantially identical in critical dimensions and performance.
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公开(公告)号：US11732645B2
公开(公告)日：2023-08-22
申请号：US17367774
申请日：2021-07-06
发明人： Eric Durocher
CPC分类号： F02C6/08 , F01D9/06 , F01D17/145 , F05D2220/323 , F05D2250/231 , F05D2260/606
摘要： A gas turbine engine comprising: a duct extending about an axis, the duct including an outer-duct wall having an interior-duct surface circumscribing an interior of the duct and an exterior-duct surface radially outward of the interior-duct surface relative to the axis, the outer-duct wall defining an offtake opening extending from the interior-duct surface to the exterior-duct surface, the offtake opening in fluid communication between an offtake location inside the duct and outside the duct, and a bleed air offtake assembly including: an air line in fluid communication with inside the duct via the offtake opening, the air line having a first-line end defining a line inlet proximate to the outer-duct wall and a second-line end spaced from the first-line end; a valve located outside the duct and fluidly connected to the air line via the second-line end, and a conduit having a conduit inlet in fluid communication with inside the air line at a resonance location between the first-line end and the second-line end upstream of the valve, and a conduit outlet in fluid communication with inside the duct at a relief location spaced from the offtake location.
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公开(公告)号：US11698005B2
公开(公告)日：2023-07-11
申请号：US17155707
申请日：2021-01-22
发明人： John S. Tu , Robert Newman , Paul K. Sanchez , Jeffrey J. Lienau , John T. Ols , Prabaharan Manoharan , Venu Sambarapu , Rajendra Prasad Uppara Allabanda
CPC分类号： F01D25/14 , F01D9/06 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2240/126 , F05D2240/81 , F05D2260/232 , F05D2260/37
摘要： Flow diverters for installation in mid-turbine frame systems at a conduit outlet of gas turbine engines are described. The flow diverters include a diverter body having a connector portion defining a diverter inlet, a diverter extension at least partially defining a diverter outlet, and a curved portion arranged between the connector portion and the diverter extension, the curved portion configured to change a direction of flow from a first direction to a second direction that is about 90° from the first direction as the flow passes from the diverter inlet to the diverter outlet.
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公开(公告)号：US20190186417A1
公开(公告)日：2019-06-20
申请号：US16219323
申请日：2018-12-13
申请人： MTU Aero Engines AG
发明人： Guenter Ramm , Martin Hoeger , Irene Raab , Yavuz Guendogdu
CPC分类号： F02K3/06 , F01D5/142 , F01D5/143 , F01D5/146 , F01D9/041 , F01D9/06 , F01D9/065 , F01D25/24 , F05D2240/12 , F05D2240/14 , F05D2250/37
摘要： The present invention relates to a turbine module for a turbomachine, comprising a first flow bypass structure and a second flow bypass structure, said flow bypass structures being arranged in a hot gas duct, which is bounded by the turbine module and is designed to convey a hot gas and, namely, being arranged in succession in relation to a longitudinal axis of the turbine module in a direction of rotation, wherein, in relation to the bypass flow in the hot gas duct, the flow bypass structures each have a leading edge, and, downstream thereto, a trailing edge, and the second flow bypass structure is provided as a deflecting blade, wherein the second flow bypass structure has a smaller profile thickness than the first flow bypass structure, and wherein the hot gas duct is enclosed by a radial width.
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