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公开(公告)号：US20240093616A1
公开(公告)日：2024-03-21
申请号：US18274645
申请日：2022-02-02
CPC分类号： F01D17/162 , F01D25/24 , F04D19/02 , F04D29/522 , F04D29/542 , F04D29/563 , F05D2220/323 , F05D2240/128 , F05D2260/60
摘要： An inner ring for supporting variable-pitch blades of an axial compressor stator of a turbomachine includes two or more ring sectors, assembled to form the inner ring, each ring sector including plural housings for receiving a pivot axis of one of the blades. At each junction plane between the ends of two successive ring sectors, an assembly pin and a cavity for receiving the assembly pin are engaged. The assembly pin is fixed on one end one of the two successive ring sectors and the cavity is formed at the end of the other of the two successive ring sectors. The cavity receives the assembly pin with a mounting clearance allowing a mounting by sliding fit, and the assembly pin is made of a material having a coefficient of thermal expansion greater than a coefficient of thermal expansion of a material constituting the successive ring sectors.
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公开(公告)号：US11933247B2
公开(公告)日：2024-03-19
申请号：US17869488
申请日：2022-07-20
申请人： Rohr, Inc.
发明人： Prafull Joshi , Srikanth Perumandla
CPC分类号： F02K1/766 , B64D29/06 , B64D29/08 , F05D2220/323 , F05D2260/30 , Y10T292/0886
摘要： A latch assembly includes a housing including a first housing portion and a second portion including. The latch assembly further includes a first latch member disposed within the first housing portion and configured for translation along the latch axis. The first latch member includes at least two rotatable arms configured to rotate between an arm retracted position and an arm extended position in which the at least two rotatable arms extend in a first direction away from the latch axis. The latch assembly further includes a second latch member disposed within the second housing portion and configured for translation along the latch axis. The second latch member includes a second latch member body including a base portion and at least one axially extending portion extending from the base portion in a second direction toward the interior surface of the lateral wall.
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公开(公告)号：US11933229B2
公开(公告)日：2024-03-19
申请号：US18165173
申请日：2023-02-06
CPC分类号： F02C7/36 , F16H57/082 , F05D2220/323 , F05D2250/75 , F05D2260/40311
摘要： Speed reduction gear for an aircraft turbomachine. The reduction gear has a main axis and planet carrier having a cage and a cage carrier, a sun gear located in the cage and centred on the main axis, an annular row of planet gears arranged around the main axis and the sun gear and meshed with the sun gear, and a ring gear arranged around the axis and the cage and meshed with the planet gears. The cage and the cage carrier are connected to each other by connections whose bending flexibility is optimised.
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公开(公告)号：US20240084742A1
公开(公告)日：2024-03-14
申请号：US17942529
申请日：2022-09-12
CPC分类号： F02C9/32 , B64D31/00 , B64D45/00 , B64D2045/0085 , F05D2220/323 , F05D2220/329
摘要： Various implementations described herein are related to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to reduce fuel consumption of at least one engine of the multiple engines during reduced-engine operation by pulse modulating fuel delivery to the at least one engine of the multiple engines.
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公开(公告)号：US11927402B2
公开(公告)日：2024-03-12
申请号：US17374860
申请日：2021-07-13
申请人： The Boeing Company
CPC分类号： F28D7/022 , B64D33/02 , F02C7/141 , F28F13/12 , B64D2033/024 , F05D2220/323 , F05D2220/76 , F28D2021/0021
摘要： Systems, apparatuses, and methods relating to heat transfer devices having nested layers of helical fluid channels. In some examples, a device for transferring heat includes a set of nested tubular walls and a plurality of helical walls intersecting each of the nested tubular walls to form one or more first channel layers nested with one or more second channel layers. Each of the first and second channel layers includes a plurality of helical fluid channels. A first intake and a first outtake are in fluid communication with one another via the plurality of helical fluid channels of each first channel layer, for flow of a first fluid through the device. A second intake and a second outtake are in fluid communication with one another via the plurality of helical fluid channels of each second channel layer, for flow of a second fluid through the device.
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公开(公告)号：US11927109B2
公开(公告)日：2024-03-12
申请号：US17785572
申请日：2020-12-08
申请人： MTU Aero Engines AG
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/142 , F05D2220/323 , F05D2240/12 , F05D2240/301 , F05D2250/70
摘要： The present invention relates to a blade for a gas turbine, in particular of an aircraft engine, having a blade airfoil, which has a blade-root-side first profile section and a blade-tip-side second profile section, which is spaced apart from the first profile section in a radial direction, from the first profile section to the second profile section, by a blade airfoil height, wherein a stagger angle of the blade airfoil changes with a height in the radial direction over the first profile section at least over certain portions, wherein, in a first region between a first height and a second, greater height, the change in the stagger angle over the height does not decrease with increasing height at least over certain portions.
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公开(公告)号：US20240077019A1
公开(公告)日：2024-03-07
申请号：US18233518
申请日：2023-08-14
申请人： ROLLS-ROYCE plc
CPC分类号： F02C7/16 , F02C6/18 , F05D2220/323 , F05D2260/213
摘要： A thermal management system for an aircraft includes a first gas turbine engine, first thermal bus, first heat exchanger, one or more first ancillary systems, vapour compression system, one or more second ancillary systems and second heat exchanger. A waste heat energy generated by a first gas turbine engine, and a first ancillary system, transfers to the first heat transfer fluid. A waste heat energy generated by a second ancillary system transfers to a second heat transfer fluid, and the second heat exchanger transfers the waste heat energy from the second heat transfer fluid to the first heat transfer fluid. The waste heat energy generated by a second ancillary system transfers to the first heat transfer fluid, and the first heat exchanger transfers the waste heat energy to a dissipation medium. The waste heat energy transferred to the second heat transfer fluid ranges from 20 kW to 300 kW.
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公开(公告)号：US20240076034A1
公开(公告)日：2024-03-07
申请号：US17902261
申请日：2022-09-02
CPC分类号： B64C21/08 , F02C6/08 , B64C2230/06 , F05D2220/323 , F05D2260/605 , F05D2260/606
摘要： An assembly is provided that includes a regulator manifold and a regulator element. The regulator manifold includes an inlet passage, a first outlet passage and a second outlet passage. The inlet passage is configured to receive bleed gas from a core flowpath. The regulator element is within the regulator manifold and configured to pivot to a first position, a second position and an intermediate position between the first position and the second position. The regulator element is configured to fluidly couple the inlet passage with the first outlet passage in the first position. The regulator element is configured to fluidly couple the inlet passage with the second outlet passage in the second position. The regulator element is configured to fluidly decouple the inlet passage from the first outlet passage and the second outlet passage in the intermediate position.
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公开(公告)号：US11920499B2
公开(公告)日：2024-03-05
申请号：US18122807
申请日：2023-03-17
申请人： ROLLS-ROYCE plc
CPC分类号： F01D9/041 , F01D9/04 , F01D17/162 , F02C7/042 , F05D2220/32 , F05D2220/323 , F05D2240/12
摘要： A gas turbine engine includes: a fan rotating about an engine main axis; a core duct; an engine core; an Engine Section Stator (ESS) including a plurality of ESS vanes and arranged in the core duct downstream of the fan; and a plurality of variable inlet guide vanes (VIGV) adapted to rotate about a pivot axis and arranged in the core duct downstream of the ESS. The VIGV vanes are arranged angularly rotated with respect to the ESS vanes such that the VIGVs are shielded by the ESS, thereby protecting the VIGVs from icing and from ice shedding from the ESS vanes.
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公开(公告)号：US11913352B2
公开(公告)日：2024-02-27
申请号：US17545874
申请日：2021-12-08
发明人： Li Zheng , Nicholas Kray
CPC分类号： F01D5/147 , F01D5/18 , F05D2220/323 , F05D2230/23 , F05D2260/36
摘要： Cover plate connections for a hollow fan blade are disclosed. An example fan blade includes a hollow body including a surface defining an airfoil, the hollow body including an aperture extending through the surface, a cover plate, and at least one connection element to couple the cover plate to the surface such that the cover plate encloses the aperture.
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