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公开(公告)号：US20230140261A1
公开(公告)日：2023-05-04
申请号：US17917800
申请日：2021-03-25
摘要： A mold for manufacturing a turbomachine fan casing of composite material, includes a mandrel around which a fibrous preform of the fan casing is to be wound; counter-mold angular sectors assembled on the external contour of the mandrel which are intended to close the mold and to compact the fibrous preform wound on the mandrel; wherein each angular sector includes a first lateral flange positioned at the first end of the angular sectors and a second lateral flange positioned at a second end of the angular sectors, the first and second lateral flanges cooperating respectively with the second and first lateral flanges of the adjacent angular sectors. An angular sector includes a first groove formed in the first of second lateral flange, a first seal being positioned in the first groove, the first seal to be compressed between the first and second lateral flanges of two adjacent angular sectors.
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公开(公告)号：US20230136870A1
公开(公告)日：2023-05-04
申请号：US17452917
申请日：2021-10-29
发明人： David MENHEERE , Daniel ALECU
IPC分类号： F01D25/24
摘要： An aircraft engine comprises a casing extending circumferentially around a central axis. A support flange is secured to the casing and extends circumferentially around the axis. The support flange has an inner and an outer flange face. A component is drivingly engaged by a shaft of the engine. The component has a connecting section extending around the central axis. The connecting section has a connecting face. The inner flange face is in abutment against the connecting face. A retaining ring extends circumferentially around the central axis. The retaining ring is in abutment against the outer flange face of the support flange. The retaining ring has a coefficient of thermal expansion, which is less than that of the support flange.
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公开(公告)号：US11639671B2
公开(公告)日：2023-05-02
申请号：US17368214
申请日：2021-07-06
IPC分类号： F01D25/24
摘要： An unducted fan turbine engine comprising an engine core including a first airflow, and a nacelle circumscribing at least a portion of the engine core and having an exterior surface defining a second airflow. The nacelle further comprising an internal passage between the exterior surface and the engine core, the internal passage defining a third airflow. The unducted fan turbine engine further comprising a plurality of rotatable fan blades extending radially beyond the exterior surface of the nacelle, and a cowl door located in the nacelle.
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公开(公告)号：US20230127925A1
公开(公告)日：2023-04-27
申请号：US18088196
申请日：2022-12-23
发明人： Anthony R. Bifulco , David A. Topol
摘要： A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A fan case surrounds the fan rotor. A core engine has a compressor section and includes a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of aft connecting members rigidly connected to the fan case, and to the core engine. A plurality of fan exit guide vanes are rigidly connected to the fan case, with the fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to the core engine, and non-structural fan exit guide vanes, and the non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise.
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公开(公告)号：US11635026B1
公开(公告)日：2023-04-25
申请号：US17721779
申请日：2022-04-15
摘要： Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface and an outer surface, a front acoustic panel having an outer surface, and attachment means attaching the front acoustic panel outer surface to the fan case inner surface. The attachment means comprise a sliding arrangement allowing the front acoustic panel to be slid axially into the fan case. The sliding arrangement comprises a first longitudinal member and a second longitudinal member, one of the members being attached to the fan case inner surface and the other member being attached to the front acoustic panel outer surface. The attachment means further comprise removable fastening means fixing the first longitudinal member and the second longitudinal member in the axial direction.
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公开(公告)号：US20230122853A1
公开(公告)日：2023-04-20
申请号：US17917453
申请日：2021-03-24
摘要： A mold for manufacturing a turbomachine fan casing made of composite material, includes a main axis mandrel around which a fibrous preform of a fan casing is intended to be wound; a plurality of counter-mold angular sectors assembled on the outer contour of the mandrel which are intended to close the mold and to compact the fibrous preform wound on the mandrel; wherein a flat seal with a main elongation axis directed along the main axis is arranged between each angular sector, the flat seal being compressed between two adjacent angular sectors, a first angular sector including a sealing portion passing below a lower face of the flat seal while a second angular sector including a sealing portion passing above an upper face of the flat seal.
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公开(公告)号：US20230118738A1
公开(公告)日：2023-04-20
申请号：US17913917
申请日：2021-03-22
发明人： Clément JARROSSAY , Clément Emile André CAZIN , Sébastien Serge Francis CONGRATEL , Antoine Claude Michel Etienne DANIS , Aurélien GAILLARD
摘要： The invention relates to a turbine assembly comprising: a plurality of ring sectors forming a ring; a support structure comprising a shroud from which there project radial flanges which serve to hold latching tabs of each ring sector; a stator positioned downstream of said ring and comprising a blade provided with a radially outer platform and extending axially opposite said ring; an annular space being defined between the ring, the support structure and the platform, this annular space having passing through it a leakage air current, the assembly comprising a hollow ring which occupies said annular space and which is shaped so as to collect, channel and expel said leakage air current, more specifically to channel and expel it into the radially inner region of said annular space.
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公开(公告)号：US20230097337A1
公开(公告)日：2023-03-30
申请号：US17857594
申请日：2022-07-05
发明人： Eui Jun JU
摘要： An apparatus for disassembling and assembling a lower vane carrier and a method for disassembling and assembling the lower vane carrier by using the apparatus are proposed. The apparatus includes a rolling jig that is mounted on the lower vane carrier mounted inside a lower turbine casing, a bolt member that passes through a region where the rolling jig and the lower vane carrier are in contact with each other, and a block member mounted adjacent to the bolt member and configured to prevent the bolt member from being separated.
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公开(公告)号：US11614036B2
公开(公告)日：2023-03-28
申请号：US17530544
申请日：2021-11-19
发明人： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
IPC分类号： F02C7/36 , F02C3/107 , F02C9/18 , F02K3/06 , F02K3/075 , F01D5/06 , F01D25/24 , F02C3/04 , F02C7/20 , F04D19/02 , F01D11/12
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a circumferential array of blades, a low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area and a low pressure turbine section. The low pressure turbine section includes a maximum gas path radius, the blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the blades is equal to or greater than 0.35, and is less than 0.55.
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公开(公告)号：US20230080666A1
公开(公告)日：2023-03-16
申请号：US17800056
申请日：2021-02-18
发明人： Hayato HIROTA , Tateki SAKIMOTO , Atsunori ARAI , Tatsuya OKUWA , Hikaru MAESATO
摘要： In a flange cooling structure of a gas turbine engine, one of a first flange and a second flange is a high pressure flange that faces a first region, and the other of the first flange and the second flange is a low pressure flange that faces a second region. A contact surface of the high pressure flange or a contact surface of the low pressure flange includes a cooling groove that communicates with the first region and the second region.
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