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公开(公告)号：US09988930B2
公开(公告)日：2018-06-05
申请号：US14924042
申请日：2015-10-27
Applicant: ROLLS-ROYCE PLC
Inventor： David Andre Elysee
CPC classification number: F01D21/003 , F01D19/00 , F01D21/14 , F02C9/26 , F04D27/001 , F04D27/0292 , F05D2200/12 , F05D2220/3216 , F05D2260/821 , F05D2270/101 , F05D2270/3013 , F05D2270/44
Abstract: A method of predicting the condition of a compressor with respect to rotating stall is disclosed. The method comprises the steps of: i) comparing the difference between the largest and smallest values of a variable occurring during a time period with a difference threshold, the variable at any given time being dependent on the compressor exit pressure at that time, and ii) predicting either that the compressor is in rotating stall or that the compressor is not in rotating stall in dependence upon the result of the comparison.
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公开(公告)号：US09988924B2
公开(公告)日：2018-06-05
申请号：US14554094
申请日：2014-11-26
Applicant: ROLLS-ROYCE PLC
Inventor： Marko Bacic , Leo Vivian Lewis , Robert John Irving
CPC classification number: F01D11/24 , F01D5/06 , F01D9/02 , F01D25/12 , F01D25/24 , F05D2220/32 , F05D2240/55 , F05D2260/20
Abstract: A gas turbine engine comprising first and second axially spaced turbine rotor stages (46, 48) and a turbine casing (56) radially outside the rotor stages. A first seal segment arrangement (58) forms a cavity (64) radially between the first turbine rotor stage (46) and the turbine casing (56). A first air source (82) is coupled to the first seal segment arrangement (58). A second seal segment arrangement (70) forms a cavity (74) radially between the second turbine rotor stage (48) and the turbine casing (56). A heating chamber (84) is provided radially between the second seal segment arrangement (70) and the turbine casing (56). A duct (86) is coupled between the first air source (82) and the heating chamber (84).
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公开(公告)号：US09982688B2
公开(公告)日：2018-05-29
申请号：US14876113
申请日：2015-10-06
Applicant: ROLLS-ROYCE PLC
Inventor： Ning Wang , Ewan F Thompson
CPC classification number: F04D29/644 , F01D9/042 , F01D17/162 , F04D19/002 , F04D27/002 , F04D29/542 , F04D29/563 , F05D2250/13 , F05D2300/43
Abstract: The present invention provides a mounting arrangement for mounting a variable stator vane within a gas turbine engine. The mounting arrangement comprises an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot. The or each insert has at least one bore for receiving a spindle portion of the variable stator vane. The at least one insert is formed of a plastics material and/or the slot and the at least one insert each have a respective axial cross section with a respective first width (axial dimension) which is greater than and radially inwards from a respective second width, the first width of the at least one insert being greater than the second width of the slot and there being a smooth transition between the respective first and second widths.
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公开(公告)号：US20180130579A1
公开(公告)日：2018-05-10
申请号：US15680879
申请日：2017-08-18
Applicant: ROLLS-ROYCE plc
Inventor： Raju V. RAMANUJAN , Harshida G. PARMAR , Tan XIAO
CPC classification number: H01F1/0573 , B22F1/0044 , B22F3/02 , B22F3/24 , B22F9/24 , B22F2003/248 , B22F2201/20 , B22F2202/11 , B22F2301/355 , B22F2304/054 , C22C33/0235 , C22C38/002 , C22C38/005 , C22C38/06 , C22C38/10 , C22C2200/04 , C22C2202/02 , H01F1/0553 , H01F41/0253
Abstract: A process for producing Co, Al alloyed NdFeB nanoparticles, by a microwave assisted combustion process, followed by a reduction diffusion process, includes the steps of: preparing a first solution of boric acid dissolved in 4 N HNO3, dissolving iron nitrate nonahydrate, neodymium nitrate hexahydrate, cobalt nitrate hexahydrate, aluminium nitrate, the first solution in deionized water to form a second solution, adding glycine to the second solution in a molar ratio of 1:1 to form a third solution, subjecting the third solution to microwave radiation, thereby forming an first powder of NdFeCoAlB oxides, mixing the first powder with calcium hydride in a mass ratio of 1:1.1 (NdFeCoAlB oxides:CaH2) to form a second powder, compacted into a powder block, annealing the second powder in a vacuum furnace, washing the annealed second powder with a solution of ethylenediaminetetraacetic acid; and vacuum drying the second powder.
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公开(公告)号：US09965571B2
公开(公告)日：2018-05-08
申请号：US14265843
申请日：2014-04-30
Applicant: ROLLS-ROYCE PLC
Inventor： Paul Hield , James Page , Paul Tucker
CPC classification number: G06F17/50 , F01D5/141 , F01D9/02 , F05D2260/81 , G06F17/5018 , G06F2217/46 , Y02T50/673
Abstract: A method of recambering an aerofoil section. A position on one of the surfaces that intersects with a passage shock between adjacent aerofoils is determined and then projected as a shock position onto the camber line. A shock region encompassing the shock position and extending in a chordal direction towards the leading and trailing edges is defined. The camber line is recalculated in an upstream region using semi-inverse design. The camber line is extrapolated across the shock region to match a geometric criterion. The camber line is recalculated in a downstream region using semi-inverse design.
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Patent Agency Ranking
公开(公告)号：US09963221B2
公开(公告)日：2018-05-08
申请号：US14692308
申请日：2015-04-21
Applicant: ROLLS-ROYCE PLC
Inventor： Christopher Michael Grice
CPC classification number: B64C11/06 , B64C11/306 , B64C11/48 , F16C19/24
Abstract: Unison ring system includes first unison ring portion, second unison ring portion, and bearing. Second unison ring portion is co-axial with first unison ring portion. First unison ring portion includes first unison ring and first bearing location portion and second unison ring portion includes second unison ring and second bearing location portion. First bearing location portion is co-axial with first unison ring and projects axially from first unison ring, while second bearing location portion is co-axial with second unison ring and projects axially from second unison ring. First bearing location portion includes outwardly opening groove, and second bearing location portion includes inwardly opening groove. First unison ring portion and second unison ring portion positioned with first bearing location portion being concentric with second bearing location portion defining annular cavity there between. Bearing is accommodated in annular cavity, with axial length of annular cavity being greater than axial length of bearing.
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公开(公告)号：US20180119554A1
公开(公告)日：2018-05-03
申请号：US15855594
申请日：2017-12-27
Applicant: ROLLS-ROYCE PLC
Inventor： Bogachan ALPAN
Abstract: A method locates and maintains a core in fixed space relationship within the interior of a shell mould. The method provides at least one pin extending into the core with at least one axial end of the pin protruding from the core. A wax pattern having an outer surface is formed by encasing the core and at least one protruding axial end of the pin in wax such that at least one protruding axial end of the pin terminates at the outer surface of the wax pattern. A shell mould is formed around the wax pattern such that, upon removal of the wax pattern, and in a subsequent casting process for production of hollow metal components, at least one protruding axial end of the pin abuts the shell mould, thus fixing the pin and maintaining a position of the core relative to the mould. The protruding axial end of the pin has an enlarged head.
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公开(公告)号：US09957835B2
公开(公告)日：2018-05-01
申请号：US14846323
申请日：2015-09-04
Applicant: ROLLS-ROYCE PLC
Inventor： Dale Edward Evans
CPC classification number: F01D21/045 , F01D25/24 , F01D25/246 , F05D2220/36 , F05D2230/60 , Y02T50/672
Abstract: A fan track liner assembly for a ducted fan engine which provides for ease of installation and replacement. The assembly includes a plurality of panels; and a plurality of fastening members which are arranged to secure the panels to the fan case of the engine, wherein: each fastening member has a base portion and an elongate arm member, and further wherein: the base portion has an attachment portion which is used to secure the fastening member to the fan case; and the arm member extends from the base portion, and each panel has slotted edge portions on opposing edges at one end of the panel which are each arranged to engage with respective arm members of fastening members on either side of the panel when the panel is assembled with the fastening members by sliding the panel onto the fastening members or vice-versa.
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公开(公告)号：US09956653B2
公开(公告)日：2018-05-01
申请号：US14592518
申请日：2015-01-08
Applicant: ROLLS-ROYCE PLC
Inventor： Craig Wilson , Michael John Davey , David Cowherd , Stephen John Wilkinson
CPC classification number: B23P15/04 , B21D53/78 , B23K20/002 , B23K20/02 , B23K2101/001 , F01D5/147 , F01D5/288 , F04D29/324 , F05D2240/303 , F05D2240/304 , Y10T29/49321 , Y10T29/49337
Abstract: A method of manufacture of a cladding body for an edge of an aerofoil, the method including the step of providing a core member shaped to include an elongate recess portion for mounting on the edge of the aerofoil, the elongate recess portion being shaped across its width to define a smoothly curved concave surface. A support member is provided; the support member has a support portion for complementary engagement with the recess portion. Both the support member and the core member are arranged between a pair of opposing membranes. The core member is bonded to each of the pair of membranes to form an intermediate cladding body, wherein the recess portion of the core member is arranged to engage, at least during the bonding step, the support portion to be supported thereby. At least the membranes are shaped using a hot forming process.
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公开(公告)号：US09950388B2
公开(公告)日：2018-04-24
申请号：US14943675
申请日：2015-11-17
Applicant: ROLLS-ROYCE PLC
Inventor： Nigel James David Chivers
IPC: B23K26/00 , B23K26/342 , B23K26/144 , B23P15/00 , B22F5/04 , F01D5/14 , F01D5/34 , F01D5/18 , B23K101/00 , B23K103/14 , B23K103/18 , F01D5/30
CPC classification number: B23K26/0093 , B22F5/04 , B22F2998/10 , B23K26/144 , B23K26/342 , B23K2101/001 , B23K2103/14 , B23K2103/26 , B23P15/006 , F01D5/147 , F01D5/18 , F01D5/3061 , F01D5/34 , F05D2230/31 , Y02P10/295 , B22F3/1055 , B22F3/17
Abstract: There is proposed a method of producing an integrally bladed rotor, preferably a so-called “blisk” for a turbomachine, the method including the steps of: providing a rotor disc having a plurality of spaced-apart radial protrusions formed integrally around its perimeter; and forming a respective aerofoil-shaped blade extending radially generally outwardly from each of the protrusions via laser deposition. Each protrusion preferably extends radially outwardly from a circumferential body part of the rotor disc by a distance which is greater than the radially inward penetration of a heat-affected zone arising from the laser deposition used to form the respective blade.
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