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公开(公告)号：US20240229669A1
公开(公告)日：2024-07-11
申请号：US18561861
申请日：2022-05-13
IPC分类号： F01D11/00
CPC分类号： F01D11/008 , F05D2220/36 , F05D2300/603
摘要： The present invention relates to a platform for a fan assembly, comprising a flow passage wall extending in an axial direction having an upstream end and a downstream end, and comprising two axial stiffeners. The platform comprises radial retention means positioned at the upstream end and at the downstream end of the flow passage wall, the radial retention means being designed to each define a sliding connection with a corresponding shroud of the fan assembly and in that it comprises tangential retention means designed to define a sliding pivot connection between the platform and a disc of the fan assembly.
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公开(公告)号：US20240141794A1
公开(公告)日：2024-05-02
申请号：US17976345
申请日：2022-10-28
CPC分类号： F01D5/30 , F01D11/008 , F05D2220/32 , F05D2240/80 , F05D2250/70 , F05D2300/514
摘要： A rotor assembly is provided that includes a rotor disk, a rotor blade and a rotor spacer. The rotor disk includes a slot. The rotor blade includes a blade root arranged within the slot. The root spacer is arranged within the slot between the rotor disk and the blade root. The root spacer is configured as or otherwise includes a cellular structure with a plurality of internal cells.
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公开(公告)号：US20230399956A1
公开(公告)日：2023-12-14
申请号：US18456126
申请日：2023-08-25
申请人： RTX CORPORATION
发明人： Jason Husband , James Glaspey , Aaron John Pepin
CPC分类号： F01D5/3053 , F01D5/147 , F01D5/282 , F01D11/008 , F01D5/02 , F01D5/3038 , F05D2240/301 , F05D2240/80 , F05D2260/30 , F05D2300/603 , F05D2300/702 , F05D2260/31
摘要： A rotor assembly for a gas turbine engine includes a rotatable hub that has a main body and an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels. An array of airfoils are circumferentially distributed about the outer periphery. Each one of the airfoils includes an airfoil section extending from a root section received in the annular channels. Retention pins extend through the root section of a respective one of the airfoils and through the array of annular flanges to mechanically attach each root section to the hub.
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公开(公告)号：US20180347380A1
公开(公告)日：2018-12-06
申请号：US15988386
申请日：2018-05-24
CPC分类号： F01D5/225 , F01D5/28 , F01D11/008 , F05D2240/80 , F05D2260/30 , F05D2260/95 , F05D2300/17
摘要： The invention relates to an assembly comprising: a movable blade (100) for a turbomachine comprising a root (130), a removable part (300) comprising an anti-wear material, configured to be attached removably to an edge of the root (130) to limit wear of the root (130).
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公开(公告)号：US10018066B2
公开(公告)日：2018-07-10
申请号：US14862342
申请日：2015-09-23
发明人： Philip Robert Rioux
CPC分类号： F01D11/008 , F01D5/02 , F01D5/225 , F01D9/041 , F01D11/005 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2240/80 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/71 , F05D2250/75 , Y02T50/672 , Y02T50/673
摘要： What is described is a partial platform. The partial platform includes a leading edge, a trailing edge, a first circumferential edge and a second circumferential edge. The first circumferential edge and the second circumferential edge are both swept such that a central circumferential axis forms a substantially rounded or squared S shape.
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公开(公告)号：US20180187558A1
公开(公告)日：2018-07-05
申请号：US15397501
申请日：2017-01-03
发明人： Charles Thistle , Mohamed Hassan
CPC分类号： F01D5/225 , F01D5/02 , F01D5/22 , F01D5/3007 , F01D11/006 , F01D11/008 , F04D29/083 , F04D29/322 , F04D29/324 , F04D29/668 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/60 , F05D2240/80 , F05D2260/36 , Y02T50/673
摘要： A blade for a gas turbine engine is provided. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; and a chamfer located on opposing peripheral edges of the platform.
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公开(公告)号：US09920636B2
公开(公告)日：2018-03-20
申请号：US14499386
申请日：2014-09-29
发明人： Herbert Brandl
CPC分类号： F01D5/22 , F01D5/147 , F01D5/3007 , F01D5/326 , F01D11/008 , F05B2240/57 , F05D2230/50 , F05D2230/51 , F05D2240/55 , F05D2240/57 , F05D2240/80 , F05D2260/30 , F05D2260/31 , F05D2260/36 , F05D2260/96
摘要： The invention relates to a turbine blade, including a blade having a front edge and a rear edge, which blade transitions by means of a shaft into a blade root designed for fastening the turbine blade, and including a platform, which is arranged at the lower end of the blade in order to bound a flow channel. The platform is designed as a separate component and can be connected to the blade in a form-fit manner. Flexible application is achieved in that the platform is composed of several individual platform elements, which enclose the blade in the assembled state.
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公开(公告)号：US09920627B2
公开(公告)日：2018-03-20
申请号：US14712988
申请日：2015-05-15
CPC分类号： F01D5/082 , F01D5/081 , F01D11/008 , F01D17/105 , F04D19/002 , F04D25/045 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2260/2212 , F05D2260/231 , Y02T50/676
摘要： An assembly for a gas turbine that engine includes a fan section. A turbine section is configured to drive the fan section. The turbine section includes a rotor hub with a rotor lug. A heat shield engages the rotor lug. The heat shield and the rotor lug define a cooling passage.
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公开(公告)号：US09845699B2
公开(公告)日：2017-12-19
申请号：US13833162
申请日：2013-03-15
CPC分类号： F01D11/008 , B29C45/14 , B29C70/68 , F05D2220/36 , F05D2250/11 , F05D2300/603 , Y02T50/672
摘要： A fan spacer for placement between a pair of adjacent blades in a fan assembly and a related method of making. The fan spacer has a spacer body including an airflow surface shaped to direct air between the pair of adjacent blades in which the airflow surface is shaped on opposing sides to correspond to the pair of adjacent blades. An over molded feature is molded onto the airflow surface of the spacer body in which the over molded feature both includes an erosion coating on the airflow surface and, on the two opposing sides, seals configured to seal against the pair of adjacent blades on the opposing sides of the airflow surface.
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公开(公告)号：US09828861B2
公开(公告)日：2017-11-28
申请号：US14428706
申请日：2013-09-17
发明人： Son Le Hong
CPC分类号： F01D5/282 , F01D5/147 , F01D5/3038 , F01D5/3084 , F01D11/008 , F05D2220/30 , F05D2230/30 , F05D2230/60 , F05D2240/24 , F05D2300/20 , F05D2300/2261 , F05D2300/437 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： A turbine engine blade made of composite material including fiber reinforcement obtained by three dimensionally weaving yarns and densified with a matrix, the blade including an airfoil and a blade root forming a single part. The blade root includes two opposite lateral flanks that are substantially plane and that are clamped between two independent pads made of composite material, which pads are fastened against the lateral flanks of the blade root to form a blade root that is bulb-shaped.
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