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公开(公告)号：US11885239B2
公开(公告)日：2024-01-30
申请号：US17776103
申请日：2020-11-18
CPC分类号： F01D5/282 , F01D5/147 , F05D2300/6034
摘要： The invention relates to a turbomachine rotary-fan blade having a predetermined breaking zone, which extends from the upstream edge along a given length and from the blade-tip edge over a given height. According to the invention, the body is made of a composite material comprising a fibre reinforcement obtained by three-dimensional weaving of warp and weft strands, and a resin matrix in which the fibre reinforcement is embedded, and has, in or in the vicinity of the zone, a discontinuity of at least some of the strands, configured such that the zone partially detaches when there is tangential friction in the thickness direction against the blade-tip edge, the height being less than 3% of the aerodynamic stream height of the blade.
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公开(公告)号：US11753949B2
公开(公告)日：2023-09-12
申请号：US17798453
申请日：2021-02-01
CPC分类号： F01D5/282 , D03D25/005 , F01D5/147 , F05D2220/323 , F05D2240/30 , F05D2300/603 , F05D2300/6012
摘要： A fibrous texture intended to form the fibrous reinforcement of a turbomachine blade made of composite material including a fibrous reinforcement densified by a matrix, wherein the fibrous texture includes an area of reduced stiffness including warp yarns or strands made of second fibers having a second elongation at break greater than the first elongation at break, the area of reduced stiffness extending in the longitudinal direction from the stilt area and up to a height less than or equal to 30% of the height of the blade, extending in the transverse direction between a first area and a second area, the first area extending over a first length from a first edge of the texture intended to form a leading edge, and the second area extending over a second length from a second edge of the texture intended to form a trailing edge.
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公开(公告)号：US12018589B2
公开(公告)日：2024-06-25
申请号：US18248711
申请日：2021-10-05
IPC分类号： F01D5/28
CPC分类号： F01D5/282 , F05D2220/36 , F05D2240/303 , F05D2300/603
摘要： A blade comprising a blade body made of fiber-reinforced organic-matrix composite material and a leading edge shield made of a material having a better resistance to point impacts than the composite material of the blade body, the leading edge shield being assembled on the blade body and including a pressure side fin and a suction side fin connected by a thicker central part, the blade including an aerodynamic airfoil height and a chord length, the suction side fin having a first length projected onto the chord between 10 and 18% of the chord length, the first length being disposed between 70 and 80% of the aerodynamic airfoil height, a second length projected onto the chord between 18 and 26% of the chord length, the second length being disposed between 85 and 95% of the aerodynamic airfoil height.
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公开(公告)号：US11634988B2
公开(公告)日：2023-04-25
申请号：US17312757
申请日：2019-12-10
发明人： Sadim Dieudonne , Mickaël Cavarec , Guillaume Pascal Jean-Charles Gondre , Nicolas Pierre Alain Edme De Cacqueray-Valmenier
IPC分类号： F01D5/14
摘要： A turbomachine rotor blade is formed of plural blade sections stacked along an axis extending from a blade root to a blade tip. Each blade section located at various heights along the blade is designed to have a given ratio between a maximum thickness, which is measured between a suction side and pressure side of the blade, and a chord, which is defined by a line connecting a leading edge and a trailing edge of the blade. Each blade section is further designed to have a ratio of the maximum thickness to the chord at a given height of the blade relative to a ratio of the maximum thickness to the chord of another blade section located at a different height of the blade.
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公开(公告)号：US12037924B2
公开(公告)日：2024-07-16
申请号：US17784932
申请日：2020-12-14
CPC分类号： F01D5/288 , F01D5/147 , F05D2220/32 , F05D2230/20 , F05D2230/31 , F05D2240/30
摘要： A method for manufacturing a blade from composite material having an added metal leading edge for a gas turbine aeroengine includes producing a blade body from composite material including a blade root part, a shank part and an airfoil body part; manufacturing, via additive manufacturing, a leading edge extending in a longitudinal direction between a lower end present at the shank part of the composite material and an upper end present at the tip; bonding the manufactured leading edge onto the foremost edge portion of the airfoil body of the blade body.
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公开(公告)号：US12000303B2
公开(公告)日：2024-06-04
申请号：US18039611
申请日：2021-11-29
发明人： Carole Onja Rakotoarisoa , Teddy Fixy , Guillaume Pascal Jean-Charles Gondre , Julien Paul Schneider-Die-Gross
CPC分类号： F01D5/147 , F01D5/141 , F01D5/282 , F05D2240/303 , F05D2300/6034
摘要： The invention relates to a fan blade (3) made of composite material the fibrous reinforcement of which comprises first strands (12) having a first stiffness, second strands (13) having a second stiffness and third strands (14) having a third stiffness lower than the first stiffness and greater than the second stiffness, the blade comprising a first portion (15) comprising only first strands (12), a second portion (16) comprising only second strands (13) and a third portion (17) which is located between the first and second portions (15, 16) and which comprises both first, second and third strands (12, 13, 14); there is a gradual transition of properties at the interface between the different portions (15, 16, 17).
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公开(公告)号：US11753943B2
公开(公告)日：2023-09-12
申请号：US17312212
申请日：2019-12-10
发明人： Guillaume Pascal Jean-Charles Gondre , Nicolas Pierre Alain Edme De Cacqueray-Valmenier , Mickaël Cavarec , Sadim Dieudonne
IPC分类号： F01D5/16
CPC分类号： F01D5/16 , F05D2240/301 , F05D2260/961
摘要： A turbomachine rotor blade includes plural blade sections stacked along an axis between a blade root and a blade head defining between the blade root and the blade head the height of the blade, each blade section including a chord and a maximum sweep defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of a camber line formed of all points located equidistant from the extrados and the intrados in the section, and verifying that the ratio between the maximum sweep and the chord at mid-height of the blade and the same blade head ratio is between 25% and 40% of the ratio between a maximum sweep and a blade root chord.
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公开(公告)号：US11920494B2
公开(公告)日：2024-03-05
申请号：US17913946
申请日：2021-03-24
CPC分类号： F01D5/147 , F01D5/282 , F05D2220/323 , F05D2240/30
摘要： The present invention relates to a turbomachine rotary-fan blade (2), comprising a body (20) made of a composite material, a metal reinforcement part (3) comprising a metal upstream nose (31), characterised in that the metal upstream nose (31) comprises, at least on the metal part (27b) of the blade tip, a recess (4) of longitudinally tapering thickness (AX), delimiting on the metal part (27b) over a height (H) at least one metal projection (5) with prescribed wear, which has a longitudinally tapering thickness and which is configured to detach at least partially in the presence of tangential friction in the second thickness direction (EP) against the metal part (27b), the recess (4) and the metal projection (5) with prescribed wear extending the first metal fin (32) and/or the second metal fin (33) and/or the upstream edge (22) of the body (20) made of composite material.
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公开(公告)号：US11168567B2
公开(公告)日：2021-11-09
申请号：US16596232
申请日：2019-10-08
IPC分类号： F01D5/14
摘要： A fibrous texture to form the fibrous reinforcement of a turbomachine blade made of composite material, the texture being made in one piece and having a three-dimensional weaving, and includes blade root, blade airfoil and blade support portions. The blade support portion includes a first area extending transversely from a first edge of the texture to form a leading edge and a second area extending transversely from the first area up to a second edge of the texture to form a trailing edge, the first area including warp yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than that of the first fibers, the first area having a first volume ratio in yarns or strands made of second fibers strictly greater than a second volume ratio in yarns or strands made of second fibers in the second area.
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公开(公告)号：US11098590B2
公开(公告)日：2021-08-24
申请号：US16710931
申请日：2019-12-11
发明人： Mickael Cavarec , Sadim Dieudonne , Nicolas Pierre Alain Edme De Cacqueray-Valmenier , Guillaume Pascal Jean-Charles Gondre
IPC分类号： F01D5/14
摘要： A turbine engine rotor blade including a plurality of blade cross sections stacked along an axis Z between a blade root and a blade tip defining therebetween the height of the blade, each blade cross section including a leading edge (16) and a trailing edge (17) and a chord defined by the length of the segment which extends from the leading edge to the trailing edge and ensuring that: the ratio of the chord at mid-height and of the chord at the blade root is comprised between 140% and 160%; the ratio of the chord at the blade tip and of the chord at the blade root is comprised between 115% and 135%; the chord is locally constant in a blade root zone and in a blade mid-height zone.
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