3-筛选及标引后的专利著录项目数据及专利全文us9701412b2

1、c12) United States PatentStretton et al.I 111111111111111111111111111111111111111111111111111 IIIIIIIIIII IIIIIIIIIIIIUS009701412B2(IO) Patent No.:US 9,701,412 B2(45) Date of Patent:Jul. 11, 2017(54)AIRCRAFT ENGINE MOUNTFOREIGN PATENT DOCUMENTS(71) Applicant: ROLLS-ROYCE PLC, London (GB)EP1 281 615

2、Al2/2003EP1852346 Al11/2007(72) Inventors: Richard Geoffrey Stretton,Ashby-de-la-Zouch (GB); Kenneth Franklin Udall, Derby (GB)(73) Assignee: ROLLS-ROYCE pie, London (GB)(*)Notice:Subject to any disclaimer, the term ofthispatent is extended or adjusted under 35U.S.C. 154(b) by 339 days.(21) Appl. No

3、.: 14/474,760(Continued)OTHER PUBLICATIONSMar. 25, 2014 Search Report issued in British Application No GB1315968.6(Continued)Primary Examiner - Brian M OHara(22) Filed: (65)Sep. 2, 2014Prior Publication DataAssistant Examiner - Assres H Woldemaryam(74) Attorney, Agent, or Firm - Oliff PLCUS 2015/006

4、9176 AlMar. 12, 2015(30)Foreign Application Priority DataSep. 9, 2013(GB)1315968.6(51)Int. Cl.B64D 27100(2006.01)(52)B64D 27126U.S. Cl.(2006.01)CPC . B64D 27126 (2013.01); B64D 2027/262(2013.01); B64D 2027/266 (2013.01)(58) Field of Classification SearchCPC. B64D 2027/262; B64D 2027/266; B64D27/26Se

5、e application file for complete search history(56) References CitedU.S. PATENT DOCUMENTS 5,078,342 A1/1992 Langley et al5,275,357 A * 1/1994 Seelen.B64D 27/26244/545,351,930 A * 10/1994 Gwinn.B64D 27/26244/54(Continued)1220(57) ABSTRACTAn engine mount, for mounting the casing of an aircraft engine t

6、o the fuselage or wing of an aircraft, e.g. via a pylon, including first and second links having connector formations for connection to respective mounting and support forma tions on the engine casing and aircraft mounting structure Each of the first and second links is typically connected by a pin

7、between the mounting and support formations. Each link has a further connector formation arranged such that the connector formation of the first link is offset from the connector fom 皿 ion of the second link. The connector formations are joined by an intern 记 diate link. The mount allows lateral for

8、ces and torque to be resolved in such a way as to substantially avoid lateral displacement of the engine away from a central plane. The intermediate link may also provide a failsafe catcher arrangement in the event that the first or second link fail.18 Claims, 5 Drawing Sheets了八斗，3A, 1 2 必 4118 6 15

9、US 9,701,412 B2Page 2(56)References Cited2008/0073460 Al*3/2008 Beardsley.B64D 27/26244/54U.S. PATENT DOCUMENTS2008/0230675 Al*9/2008 Audart-Noel.B64D 27/26248/5545,860,623 A *1/1999 Dunstan.B64D 27/186,059,227A5/2000Le Blaye et al6,330,995Bl*12/2001Mangeiga.B64D 27/266,341,746Bl*1/2002Pascal.244/54

10、B64D 27/266,648,271B2 *11/2003Levert.244/54B64D 27/268,328,133B2 *12/2012Suciu.244/54B64D 27/268,443,612B2 *5/2013Foster.244/54B64D 27/269,180,975B2 *11/2015Brochard.244/54B64D 27/262002/0104924Al*8/2002Roszak.B64D 27/262006/0219841Al*10/2006Dron.244/54B64D 27/262007/0138337Al*6/2007Audart-Noel.244/

11、54B64D 27/26244/53 R244/542012/0198816 Al8/2012 Suciu et al2014/0061426 Al*3/2014 ZhengB64D 27/26248/554FOREIGN PATENT DOCUMENTSEP2 133 268 A212/2009EP2 221 249 A28/2010FR2925016 Bl * 6/2010B64D 27/26GB2 224 707 A5/1990WOWO 2011159671 Al * 12/2011.B64D 27/26OTHER PUBLICATIONSJan. 22, 2015 Search Rep

12、ort issued in European Application No 14183050* cited by examinerD.s. rpatentJuJ.11, 2017 Sheet 1 of 5VS9701,42 I 2 3 20 3A x/ / / 8.3 忍心 B ，1 t A 1 认-$ /3 t ， i656 心 jli ，Fig仑 1U.S. PatentUS 9,701,412 B2Jul. 11,2017Sheet 5 of 545 l12262 . /“-、,l、 ,. 3m3B 16/ i、 f 、f(3A、,-114 、一 ，主、I 丿 、一一- - 、3、 :、

13、 55I15、7 /二二三、 、/ ,. ; ;、 i 167 25Fig. 2户 i i 、，气 3 令才 f 、/ 8 /1Fig. 3然 f心Fig. 4Fig 5Fig. 6r(口2,tO2i _ ,._ 寸上） 三三仁l一= 冬 i上I忭. 1. ， 三三、l一、-一寸 一勹- 一上一i _J* 仁二言 l:杠，甘0m。i108106Fig. 7US 9,701,412 B22 1 AIRCRAFT ENGINE MOUNTThe first and second connection formations may be offsetin that they may be space

14、d from the engine or the respective BACKGROUND OF THE INVENTIONengine support formations by different distances. The enginemay have a centre of gravity or central axis, which may This invention relates to an aircraft engine mount and 5 comprise a longitudinal axis. The first and second connec- more

15、specifically, although not exclusively, to an arrange-tion formations may be offset in that they may be located at ment for mounting a gas turbine engine to an aircraft pylon.different radial distances from said centre of gravity orA conventional mounting arrangement allows a gas tur-central axis. T

16、he first and second connection fom皿 ions may bine en ine.to e ung beneath an aircraft wing or else. be located at different heightsmounted to the fuselage.10The inwardly depending portions of the first and secondIt is a consideration in the design of aircra_ft .e.nu0g.in.e. links may take the form o

17、f levers. The inwardly depending pylons, that the pylon is not only capable of supporting theportions of the first and second links may be vertically offset,engine but also withstanding the multidirectional loadsfor example in that they may be spaced from the engine byexperienced by the engine in us

18、e and bearing ;t:h-e-nt:h-:r;u:.s.t_a-n:d_ different distances. The pairing or coupling of the intern贮 reverse thrust produced by the engine. It is an aim to 1.5-diate link between the first and second links in the mannermaintain the engine aliglllllent relative to the wing orfuselage so as to avoid

19、 off axis loading. However this aiimm ;i0sclaimed is advantageous in that it may provide a further hanipered by thermal expansion of the engine that can occurforce path and avoid a local offset couple in the engine in u;e. The mal expansion is transient d may occur in a mounting assembly between the

20、 lever portions of the firstlocalised region or regions of the engine casing rather than 20 and second linksin a uniform ma 皿 er.The first and second connection formations may be pro- Known engine mounts include two-link and three- vided on the respective first and second links.link arrangements. An

21、 example of a two-link arrangementAt least a portion of the first and second links may extend is shown in US2008/0230675Al. This comprises a mount- generally inwardly from the mounting and/or support for- ing block to which two link arms are connected. The link 25 mations towards a central or vertic

22、al plane there-between. arms generally have the form of triangular members that areThe offset arrangement of the first and second connection each pinned at two apexes to the mounting block. The free formations is beneficial in that a load experienced by only apex is pinned to the engine casing. Mult

23、iple link attachment one of the links due to local thermal expansion/loading, e.g. points allow the mounting structure to retain torque capa- in the vicinity of one engine support formation, will be bility even under failure case scenarios. This arrangement 30 communicated to the other link by the i

24、ntermediate member has the disadvantage that, if localised thermal expansion of in a mani 记 r that reacts said loading so as to withstand any the engine occurs, the casing may be displaced laterally and resultant roll torque being applied to the engine. Loads downwardly relative to one of the links,

25、 causing misalign- applied to one link only, e.g. along a link axis will pass ment with other assemblies such as the nacelle exhaust directly into the mounting formation in a substantially system.35 vertical direction with minimal loading on the remainder of An ex 皿 ple ofa three-link arrangement is

26、 shown in U.S. the systemPat. No. 5,078,342A. In this arrangement the link arms areAvertical direction or plane may be defined as a plane that straight and are pinned to the mounting block at one end and includes the engine axis and passes between the first and to the engine casing at the other. A t

27、hird straight link arm, for second mounting and/or support formationsreacting torque loads, is pinned to the casing at its centre- 40 The mounting structure of the aircraft may be, or com- line and to the mounting block at a location spaced from the prise, a pyloncasing centre-line. The presence of

28、the third link arm mayThe support structure of the engine may comprise anmitigate the lateral/downward displacement caused by local- engine casing. The support structure may comprise a rear ised them 叫 expansion. However, it can be difficult to engine casing structureaccommodate the third link arm,

29、particularly in arrange- 45 The mounting formations may comprise mount pad lugs ments in which space between the casing and the mounting The support formations may comprise casing lugsblock is limited.The first and second mounting fom 皿 ions may be located The present invention overcomes or substant

30、ially m 山t o each side of the engine axis and may be substantially gates some or all of the above-mentioned and/or otherequally spaced therefrom. The first and second support 邮advantages of the prior art.so formations may be located to each side of the engine axisand may be substantially equally spa

31、ced therefrom. The BRIEF SUMMARY OF THE INVENTIONspacing of the support formations (e.g. lateral spacing) may,or may not, be greater than that of the mounting formations. According to a first aspect of the invention there isThe support formations may be angularly spaced relative provided an engine m

32、ounting assembly, for securing an 55 to the engine axis. The support formations may be spacedaircraft engine to an aircraft, the assembly comprising: first about and/or depend from an engine casing structureand second spaced support formations on the engine; firstThe first and/or second links may ha

33、ve a mounting and second corresponding mounting formations on a mount- formation connector. The first and/or second links may have ing structure of the aircraft; and first and second links, the a support fom 画 on connector. The first and/or second links first link extending between the first support

34、 formation and 60 may extend in a first direction between the support connec-!he first m?unting fo:mation, an the s_econd l) extendin tor and the ?unting c011:11e. tor. !he.first and/o.r second l)nk between the second support formation and the second may extend in a second direction between the moun

35、ting mounting formation, the first and second links being shapedconnector and its connection formation (e.g. towards the to depend inwardly from the first and second mounting intermediate link in use). The angle between the first and formations towards respective first and second connection 65 secon

36、d directions may be an obtuse angle, for ex 皿 ple formations, wherein the first and second connection fom 卧 between 90 and 140. The first direction may be approxitions are offset and connected by an intermediate link.mately tangential to the engine casing. Alternatively, the4 3 US 9,701,412 B2angle

37、between the first and second directions could be acute, for example such that the first direction is approximately radial to the engine casing.The first and/or second link may comprise an elbow. TheA portion of the first link may extend beneath the second link or vice versa. That portion may compris

38、e the connection formation and may comprise the second load transfer por tion.first and/or second link may be generally triangular or 5The first and second connection formations may be delta- shaped. The first and/or second link may be archedarr nged in_ a linear alignment with the_engine axis. Thef

39、ii_-st: :-. -be vertically aligned.and/or may have one or more rounded apex. The first and/orand second connection formations and engine axis may be second link may be generally boomerang-shapedsubstantially vertically aligned. The intern 奾 ate link mayThe first and/or second links may be attached t

40、o any orany combination of the support formations, mounting for-10The intermediate link may be paired with the first and mations and/or intern 记:second links. The intermediate link may extend betweendiate link by a pivoting connection.(e.g. being paired with) the aircraft mounting structure andThe p

41、ivoting connection may serve as a fulcrum. The firs.t the engine support structure. The intermediate link may be and/or second links may be attached to any or any combi 一 attached between the mounting and support structures, for nation of the support formations, mounting formations and/ 15 example b

42、y pin joints. The intern 记 diate link may be coupled or intermediate link by a pin, e g: thereby forming a pin betw en th; fi;st link and mounting structure at oneend joint. Any or any combination of the links, support forma-thereof and the second link and casi g structure at its othertions or mount

43、ing formations may comprise one or more end. The intermediate link may cmiiprise a plurality ofaperture arranged to receive a pin. The one or more aperture intermediate link members, which may be commonly con- may open or extend in a direction that is parallel to the 20 nected at respective joints,

44、such as in the form of a paired engine axis. The one or more aperture may be a through bore linkin the respective link. The apertures may be circular.A connection between the intermediate link and the The apertures of the mounting formation connector and/oraircraft mounting structure and/or the engi

45、ne support struc- support fom 皿 ion connector of the first and/or second linksture may be arranged (e.g. by use of a clearance aperture) may be a close tolerance fit with the pin passing there- 25 such that the intermediate link is not weight bearing for the through.engine in nom叫 use. The connectio

46、n may be arranged to be The entire mount may be a pin jointed structure (i.e. allweight bearing for the engine in the event of a failure in the connections between the links and the engine/pylon may bemounting assembly, for example a failure of the first orpin joints). Any, any combination, or all o

47、f the joints may be second linkpinned ball joints.30An intermediiate mounting fom 画 on and/or support for-A mounting arrangement according to the invention can mation may be provided between the first and second better react loads on the engine casing, such as side, vertical mounting and/or support

48、fom 灿 ons. The intern 记 diate link and/or torsional loads and can accommodate deflection may be attached between the intern 记 diate mounting and resulting from local and global thermal expansion in the support formations. The first connection formation of the engine. For example, if the rear engine

49、casing structure 35 first link may be connected to one of the intermediate expands due to the hot exhaust gas, the casing rear casing mounting formation and the support formation. The second structure will expand uniformly, displacing the engine connection formation of the second link may be connect

50、ed mounting formations radially outwards. If this occurs in the to the other of the intermediate mounting formation and the vicinity of the first support formation, the first link may be support formationurged to in a clockwise sense about its mounting formation. 40 The intermediate link may be conn

51、ected to both the first The offset arrangement of the first and second links relative link and the intermediate mounting formation by a common to the intermediate link urges the second link anticlockwise pin. The intermediate link may be connected to both the about its mounting fom 皿 ion, thereby ac

52、commodating a second link and the support formation by a common pin. The corresponding displacement to the second support forma- intermediate link may be connected at its opposing ends to tion. This min 皿 ises, and may eliminate, lateral displace- 45 said common pin joints. One or both common pin jo

53、ints may ment of the casing due to them 叫 expansion of the structure be aligned with a longitudinal plane of the engine and/or and supporting links. The link geometry could also be engine casingoptimised so that the radial growth in the vertical sense isThe intermediate mounting formation and/or sup

54、port for- partially offset by the articulation of the supporting links,mation may have an aperture to receive a pin, wherein the thereby keeping the engine centre line at a constant position. so aperture may be sized to allow a clearance about said pin Furthermore, if the engine experiences, for example, aThe pin ma