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公开(公告)号：US20190003925A1
公开(公告)日：2019-01-03
申请号：US15635626
申请日：2017-06-28
发明人： Elena Otero , Thomas Morris , Christoph Hurzeler
CPC分类号： G01M15/02 , F01D5/12 , F01D9/02 , F01D21/003 , F04D27/001 , F04D29/324 , F04D29/542 , F05D2220/32 , F05D2260/80 , F05D2260/83 , G01M15/14 , G01N27/90 , G01N29/041 , G01N29/225 , G01N29/265 , G01N2291/2693
摘要： A scanner for inspecting a component is disclosed. The scanner may include a main body having a clamp attachable to the component, a first arm moveably attached to the main body, a first probe attached to the first arm, a first axial actuator in mechanical communication with the first arm, a second arm moveably attached to the main body, a second probe attached to the second arm, a second axial actuator in mechanical communication with the second arm, and a radial actuator in mechanical communication with the first arm and the second arm.
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公开(公告)号：US20180209281A1
公开(公告)日：2018-07-26
申请号：US15878785
申请日：2018-01-24
申请人： ROLLS-ROYCE plc
发明人： John H. BOSWELL , Andrew R. WALPOLE
CPC分类号： F01D5/3061 , B23K20/02 , B23K20/122 , B23P15/04 , F01D5/02 , F01D5/025 , F01D5/12 , F01D5/34 , F05D2220/32 , F05D2230/236 , F05D2230/239 , F05D2300/175 , Y02T50/672
摘要： A method (56) for fabricating an integral assembly (24) is disclosed. The method comprises providing (56) a first workpiece (26) having a first surface (46) and a second workpiece (28) having a second surface (50), performing a first bonding process between the first surface (46) of the first workpiece (26) and the second surface (50) of the second workpiece (28) to form a sub-assembly workpiece (48), and performing a second bonding process between a third surface (52) of the sub-assembly workpiece (48) and a fourth surface (54) of a third workpiece (30) to form the integral assembly (24). The material properties of the first workpiece (26) are different from material properties of the third workpiece (30).
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公开(公告)号：US20180161872A1
公开(公告)日：2018-06-14
申请号：US15578896
申请日：2016-04-27
发明人： Christian Brunhuber
CPC分类号： B22F3/1055 , B22F5/009 , B22F5/04 , B22F7/06 , F01D5/12 , F01D5/14 , F01D5/30 , F05D2230/234 , F05D2230/31 , F05D2300/175 , F05D2300/177 , Y02P10/295
摘要： A method for producing a turbine blade with a blade root portion, a blade aerofoil portion, adjoining the blade root portion, and a blade tip portion, adjoining the blade aerofoil portion, wherein the blade root portion, the blade aerofoil portion and the blade tip portion are connected to one another in a material-bonding manner, and wherein at least one cavity, serving as a cooling channel, extends through the blade root portion and the blade aerofoil portion, wherein at least the blade aerofoil portion is produced layer by layer by using an EBM process, and, after removing caked-on powder material from the at least one cavity, the blade tip portion is produced by using some other production technology.
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公开(公告)号：US20180066529A1
公开(公告)日：2018-03-08
申请号：US15259641
申请日：2016-09-08
CPC分类号： F01D5/3023 , F01D5/06 , F01D5/12 , F01D5/3015 , F01D5/326 , F04D19/02 , F04D25/045 , F05D2220/32 , F05D2230/60 , F05D2260/30 , F05D2260/36
摘要： An airfoil retention assembly for a gas turbine engine includes, among other things, a disk, a coverplate, and a retaining ring. The disk defines a disk axis and an array of slots for receiving airfoil blades. The coverplate is dimensioned to radially overlap the array of slots relative to the disk axis. The retaining ring includes a ring body extending circumferentially about the disk axis between first and second ring ends to define a ring length. First and second retaining features continue along first and second circumferential faces of the ring body, respectively, to define first and second lengths, respectively. At least one of the first and second lengths is less than the ring length.
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公开(公告)号：US09909429B2
公开(公告)日：2018-03-06
申请号：US14774895
申请日：2014-03-26
发明人： James Cosby , Kwan Hui , Michael A. Weisse
CPC分类号： F01D5/3007 , F01D5/12 , F01D5/141 , F01D5/28 , F01D5/30 , F01D5/3023 , F01D5/303 , F01D5/3038 , F01D5/3053 , Y02T50/671 , Y02T50/673
摘要： A blade for use in a gas turbine engine has an airfoil and a dovetail. The airfoil extends radially outwardly of the dovetail. An inner surface of the dovetail includes a slot extending along a length of the dovetail between a leading edge and a trailing edge. A rotor and a gas turbine engine are also disclose.
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公开(公告)号：US09896949B2
公开(公告)日：2018-02-20
申请号：US14862390
申请日：2015-09-23
发明人： Thomas J. Robertson
CPC分类号： F01D5/3069 , F01D5/12 , F01D5/147 , F01D5/282 , F01D5/3053 , F01D11/005 , F01D11/008 , F02K3/06 , F04D29/023 , F04D29/324 , F05D2220/36 , F05D2240/80 , F05D2240/81 , F05D2260/30 , F05D2260/36 , F05D2300/603 , Y02T50/676
摘要： A fan is provided. The fan may comprise a fan blade and a blade platform coupled to the fan blade. The blade platform may be a thermoplastic. A fan blade platform is also provided. The fan blade platform may comprise a first platform half comprising a slot at a first end of the first platform half and a first receiving member at a second end of the first platform half opposite the first end of the first platform half. A second platform half may comprise a hook. The second platform half may also include a second receiving member at a second end of the second platform half opposite the first end of the second platform half with the hook configured to interface with the slot. A pin may be configured to pass through the first receiving member and the second receiving member.
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公开(公告)号：US20170343574A1
公开(公告)日：2017-11-30
申请号：US15662528
申请日：2017-07-28
发明人： David A. Topol , Bruce L. Morin , Detlef Korte
CPC分类号： G01P3/48 , F01D5/02 , F01D5/12 , F02C3/04 , F02C3/10 , F02C7/24 , F02C7/32 , F02C7/36 , F02K3/06 , F05D2200/13 , F05D2200/14 , F05D2220/32 , F05D2220/36 , F05D2260/40311 , F05D2260/96 , Y02T50/673 , Y10T29/49236 , Y10T29/4932
摘要： A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine rotor, a compressor rotor, and a gear reduction that effects a reduction in a speed of the fan relative to an input speed from the first turbine rotor. Each of the compressor rotor and the first turbine rotor includes a number of blades in each of a plurality of blade rows, the number of blades configured to operate at least some of the time at a rotational speed, and the number of blades and the rotational speed being such that the following formula holds true for at least a plurality of the blade rows of the first turbine rotor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute, and the following formula holds true for at least a plurality of the blade rows of the compressor rotor: (number of blades×rotational speed)/60≦10000, the rotational speed being an approach speed in revolutions per minute.
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公开(公告)号：US20170321611A1
公开(公告)日：2017-11-09
申请号：US15437069
申请日：2017-02-20
发明人： David A. Topol , Bruce L. Morin
CPC分类号： F02C7/36 , F01D5/02 , F01D5/12 , F05D2220/36 , F05D2260/40311 , F05D2260/96 , Y02T50/673 , Y10T29/49236 , Y10T29/4932
摘要： A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor, and having a gear reduction ratio of greater than 2.5:1. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor: (number of blades×rotational speed)/60 sec≧5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine also disclosed.
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公开(公告)号：US09803492B2
公开(公告)日：2017-10-31
申请号：US14576919
申请日：2014-12-19
申请人： Siemens Energy, Inc.
IPC分类号： F01D11/00 , F01D5/22 , G01M1/00 , F01D5/30 , F01D5/12 , G01N21/88 , F01D21/00 , G01N21/954 , F01D25/34
CPC分类号： F01D11/006 , F01D5/12 , F01D5/22 , F01D5/30 , F01D21/003 , F01D25/34 , F05D2220/32 , F05D2260/80 , F05D2260/83 , G01M1/00 , G01N21/88 , G01N2021/9546
摘要： An optical measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one light source for emitting light that impinges on a blade surface of each blade in a row of blade assemblies. The system also includes a video device for imaging the blades as the blades rotate about the center axis. Further, the system includes a controller for controlling operation of the light source and video device. The controller detects a pixel intensity associated with each blade and a spacing between each pixel intensity wherein a change in spacing between consecutive pixel intensities indicates that a distance between consecutive blades has changed relative to the first distance thereby indicating at least one locked blade assembly.
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公开(公告)号：US20170306782A1
公开(公告)日：2017-10-26
申请号：US15137503
申请日：2016-04-25
发明人： Dilip M. Shah , Katelyn Kwoka , Alan D. Cetel , Venkatarama K. Seetharaman , Michael G. McCaffrey
CPC分类号： F01D11/08 , F01D5/12 , F01D9/041 , F01D11/005 , F01D25/005 , F01D25/12 , F05D2220/32 , F05D2230/00 , F05D2240/56 , F05D2300/175 , F05D2300/177 , F05D2300/506 , F16J15/3288 , F16J15/3292
摘要： An embodiment of a turbine assembly includes, among other possible things, a first component including a first component surface, a second component including a second component surface spaced apart from the first component surface, and a brush seal disposed between the first component and the second component. The brush seal includes, among other things, a first bristled region extending in a first direction from a backing plate, and sealingly engaging one of the first component surface and the second component surface. At least one of the backing plate and the first bristled region includes a nickel-based superalloy material having at least 40% of a Ni3(Al,X) precipitate phase, X being a metallic or refractory element other than Al.
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