3-筛选及标引后的专利著录项目数据及专利全文us2015232188a1

1、c19) United States1111111111111111IIIIIIIIIII 1111111111 11111 1111111111 11111111111111111111111111111111111111US 20150232188Alc12) Patent Application PublicationTATEIWAc10) Pub. No.: US 2015/0232188 Al(43) Pub. Date:Aug. 20, 2015(54) AIRCRAFTPublication Classification(71) Applicant: MITSUBISHI AIR

2、CRAFT(51)Int. Cl.CORPORATION, Aichi (JP)B64D27/12(2006.01)B64D29/02(2006.01)(72) Inventor: Jingo TATEIWA, Aichi (JP)(52) U.S. Cl.CPCB64D 27112 (2013.01); B64D 29102(2013.01)(21) Appl. No.: 14/614,650(57)ABSTRACT(22)(30)Filed:Feb.5,2015Foreign Application Priority DataAn aircraft with a turbofan engi

3、ne including an engine body and a fan, wherein the turbofan engine is supported on an airframe via a pylon, an igniter cable is interposed between an ignition plug of the engine and an ignition control unit that controls power supply to the lgn 山 on plug, andatleastapartFeb. 18,2014(JP). 2014-028916

4、of the igniter cable is passed through an inside of the pylon01/ ；尸沪田 424344,.,厂./f;Ii:；1l4:1 ;/; - - I,- 4 . ， 2, , j ， 了 七 知1七 夕 , - ,I /, i ,jl, j d 8 l ,jJ, ， 死,J/f4 l43, l L， 咖虚15 3 L ， 磕： ， ，_护肛 Patent Application PublicationAug. 20, 2015 Sheet 1 of 5US 2015/0232188 Al， 雪 丐 、 、 一 Ol A lZl 目习吟、

5、目 l袅一 、恤 寸一一、 ar $ 、 .，、 、 J -, 0占 、气 9 IJ 令FIG. 2FADEC:-、一、，一“一，一,一、，、一一、一、一，一，一，今-、-、一、，一、，一 I!31lFUEL19!lIICONTROL UNIT ! / : - - - -一?3 - i:,i12ll321:IIIGNITION SYSTEM,.Ji!i.t 厂 l; ;i31I IGNITION CONT卢R3O3L UNIT Il; !;t !ENGINE BODYtIGNITlONl IGNITiONCOILIt巨亘三，厂 iII I之PLUGt:i34lllli-ltl;i;!i；一 一

6、 一一 今 一一一 一，一 忙4 一，一心一 人- ”一、一，一、，一生一.: ii!i. ;11 7GENERATORr1尸 ,2v0 1IIL JENGINE O|L COOLER,尸 43i.- 1 ： US20150/232188Al Aug . 20, 2015 Sh et 2 of 5 PatentpAp ilcaoitnPubclaiotn t! I!lPRECOOLER.r44ii，一，一，一，一，一 4 -，；一，夕一 _,. - ，- 、J一 ， 夕 ,._ ,_ 头，一、，iPatent Application PublicationAug. 20, 2015 Sheet

7、 5 of 5US 2015/0232188 Al4 FIG; 3 r; 3 丿35 、 、 _-、; 14 寸 4L， Sl2lM UV3H 笠芍、寸 =l )三lNO ， 臣.-、卜千,_、.- .,_.,., u9 IJ 令尸-、 s,. 、 -v ，七、 、 心 US 2015/0232188 AlAug. 20, 2015l AIRCRAFTBACKGROUND OF THE INVENTION0001 1. Field of the Invention0002 The present invention relates to a turbofan engine of an airc

8、raft.0003 2. Description of the Related Art0004 A turbofan engine of aircraft includes a fan that is rotated by power created by the engine. When the turbofan engine is operated, air is divided to an engine body and a bypass flow path inside a nacelle. Air passing through the bypass flow path and ai

9、r discharged from a nozzle of the engine body join each other to be jetted backward. Thrust is obtained as a reaction of the jet flow.0005 The turbofan engine is provided with a fuel control unit that electronically controls fuel supply, and an ignition control unit that electronically controls powe

10、r supply to an ignition plug (e.g., Japanese Patent Laid-Open No. 2006- 283621).0006 A mixture of fuel and compressed a 订 is ignited by producing a spark at the ignition plug under the control of the control units, so that the engine is ignited0007 A high voltage generated by the ignition control un

11、it including an ignition coil is supplied to the ignition plug through an igniter cable (high tension cable)0008 The ignition plug is provided in a combustion cham ber of the engine, and the ignition control unit is provided ahead of the ignition plug, e.g., on the outer periphery of a fan case.0009

12、 The igniter cable connecting the ignition plug and the ignition control unit is passed through a lower region of the bypass flow path. Each of upper and lower regions of the bypass flow path is used as an outfitting space in which engine accessories are installed.0010 In some cases, an interval bet

13、ween the nacelle and a core cowl is small because of such reasons that the engine body has a large diameter, or the diameter of the nacelle cannot be increased due to limitations on ground clearance. In this case, there is a demand for ensuring required thrust at low fuel consumption, and also ensur

14、ing a sufficient braking force at the time oflanding by reverse thrust by reducing a circum ferential dimension (width) of each of the upper and lower regions of the bypass flow path to secure a flow path sectional area meeting the required thrust.0011 However, when the widths of the outfitting spac

15、es are too small, the lower outfitting space does not have a sufficient space for passing the igniter cable, and other lines and pipes.0012 Thus, an object of the present invention is to provide an aircraft capable of obtaining required thrust at low fuel consumption, and also ensuring a sufficient

16、braking force at the time oflanding by setting wiring paths oflines and pipes at appropriate positions even when there is not a sufficient space for passing the lines and pipes due to a small interval between a nacelle and a core cowl.SUMMARY OF THE INVENTION0013 The present invention is an aircraft

17、 including a tur bofan engine including an engine body and a fan, wherein the turbofan engine is supported on an airframe via a pylon, an igniter cable is interposed between an ignition plug of the engine and an ignition control unit that controls power supplyto the ignition plug, and at least a par

18、t of the igniter cable is passed through an inside of the pylon0014 The pylon is a primary structural member provided in the airframe, and includes a pylon body typically fom记 d in a box-like shape, and a fairing that covers the pylon body 0015 Here, an inner portion of the pylon body falls under th

19、e inside of the pylon. A portion outside of the pylon body but inside of the fairing also falls under the inside of the pylon.0016 In the aircraft of the present invention, the ignition control unit is preferably installed at an upper portion of a case of the fan.0017 The aircraft of the present inv

20、ention may include an engine oil cooler that is a heat exchanger cooling engine oil used in the engine body by using air flowing out of the fan as a cold source, and a precooler that is a heat exchanger cooling bleed air from the engine body by using air flowing out of the fan as a cold source, wher

21、ein the engine oil cooler and the precooler are a 盯 anged between the pylon and the engine body.0018 Even when an interval between a nacelle and a core cowl is small, it is possible to accommodate all of required pipes and lines in upper and lower regions of a bypass flow path serving as outfitting

22、spaces and the inside of the pylon in response to a demand for ensuring required thrust at low fuel consumption and also ensuring a sufficient braking force at the time of landing by reducing circumferential dimensions (widths) of the outfitting spaces.0019 Therefore, it is possible to achieve low f

23、uel con sumption and also ensure a sufficient braking force by reduc ing the widths of the outfitting spaces to required minimum values.0020 When the ignition control unit is installed at the upper portion of the case of the fan, the igniter cable passed through the inside of the pylon can be connec

24、ted to the igni tion control unit at a position close to a front end of the pylon. The length of the igniter cable can be thereby reduced, so that weight reduction and improvement of fuel consumption of the aircraft can be achieved.BRIEF DESCRIPTION OF THE DRAWINGS0021 FIG. 1 is a schematic view ill

25、ustrating a schematic structure of a turbofan engine (a left-side engine) of an air craft according to an embodiment of the present invention; 0022 FIG. 2 is a block diagrani illustrating some of engine accessories provided in the turbofan engine;0023 FIG. 3 is a cross-sectional view taken along a l

26、ine III-III in FIG. 1;0024 FIG. 4 is a plan schematic view illustrating an upper outfitting space of a bypass flow path; and0025 FIG. 5 is a plan schematic view illustrating a lower outfitting space of the bypass flow pathDETAILED DESCRIPTION OF THEPREFERRED EMBODIMENTS0026 In the following, an embo

27、diment of the present invention is described by reference to the accompanying drawings.0027 An aircraft according to the embodiment of the present invention includes a turbofan engine 10 shown in FIG. 1.0028 The turbofan engine 10 is supported on a lower side of a main wing 11 via a pylon 40.2 0029

28、The turbofan engine 10 includes an engine body 12, a fan 13, a nacelle 14 that constitutes an outer shell of the turbofan engine 10, and a core cowl 15 that is provided on an inner side of the nacelle 14.0030 The engine body 12 includes a low-pressure com pressor, a high-pressure compressor, a combu

29、stion chamber, a high-pressure turbine, and a low-pressure turbine although the constituent elements are not shown in the drawings. The constituent elements are accommodated in an engine case 121.Ajet flow created by the engine body 12 is jetted from an exhaust nozzle 122.0031 The engine body 12 is

30、provided with engine acces sories such as a fuel control unit 19, an ignition system 30 including a plurality of ignition plugs 31 and an ignition control unit 32, a generator 20, an engine oil cooler 43, and a precooler 44 as shown in FIG. 2 as one example.0032 The fuel control unit 19 includes a f

31、uel plllllp and a plurality of valves. The fuel control unit 19 electronically controls a flow rate of fuel supplied to the engine body 12. 0033 The ignition system 30 includes the ignition plugs 31 that are located in the combustion chamber, and the igni tion control unit 32 that electronically con

32、trols power supply to the ignition plugs 310034 The ignition control unit 32 includes an ignition coil 33 and an exciter 34. A high voltage generated by the ignition coil 33 is further boosted by the exciter 34.0035 As shown in FIG. 1, the ignition control unit 32 is installed on the outer periphery

33、 of a case 131 of the fan 13 in order to be grounded. The high voltage is applied to the ignition plugs 31 via an igniter cable 35. To ensure redun dancy, two igniter cables 35 (only one of which is shown) are used.0036 The igniter cables 35 are wired apart a predeter mined distance from other elect

34、ric lines in order to avoid electromagnetic interference in electric lines arranged around the igniter cables 35. The igniter cables 35 are also wired apart a predetermined distance from other structures including pipes and lines such that heat emitted from the igniter cables 35 is not accumulated.0

35、037 When a mixture of fuel and compressed air is ignited by producing sparks at the ignition plugs 31 under the control of the fuel control unit 19 and the ignition control unit 32, the engine body 12 is ignited0038 The engine body 12 is also provided with a FADEC 21 (full authority digital engine c

36、ontrol) that controls the engine body 12 so as to obtain optimum performance in view of safety and fuel consumption by controlling the operations of the engine accessories.0039 The FADEC 21 adjusts thrust by issuing a command to the fuel control unit 19 and the ignition control unit 32 based on a le

37、ver position of a thrust lever operated by a pilot and a mode prepared for the turbofan engine 10.0040 Returning to FIG. 1, the fan 13 is arranged ahead of the engine body 12, and rotated when a rotational force of the high-pressure turbine or the low-pressure turbine of the engine body 12 is transf

38、erred.0041 The nacelle 14 includes an air inlet 16 that is located at a front end, and a cowl 17 that is provided continuously to the air inlet 16. Although not shown in the drawings, the cowl 17 includes a first cowl and a second cowl that is provided continuously to a rear side of the first cowl.

39、The second cowl is slid backward when a thrust reverser is operated.0042 As for the diameterofthe nacelle 14, the upper limit of the diameter of the nacelle 14 is determined based on ademand for ensuring a prescribed height or more between a lower portion of the nacelle 14 and the ground in order to

40、 avoid daniage to the fan 13 due to dust and foreign matter raised from the ground, and since it is difficult to extend a main landing gear in order to avoid an increase in weight. 0043 The core cowl 15 covers the engine body 12 behind the fan 13.0044 Air is introduced into the nacelle 14 from the a

41、ir inlet 16, and discharged backward by the fan 13. The air is thereby divided into a flow to be supplied to the engine body 12 in the engine case 121, and a flow (fan flow) passing through a bypass flow path 18 between the core cowl 15 and the nacelle 14 (the cowl 17).0045 The fan flow traveling ba

42、ckward from the bypass flow path 18 and the jet flow discharged from the exhaust nozzle 122 join each other to be jetted backward0046 The above thrust reverser blocks the fan flow and jets the flow forward from a gap of the cowl 17 (a gap between the first cowl and the second cowl) to thereby brake

43、the aircraft at the time oflanding.0047 Both of the nacelle 14 and the core cowl 15 described above have a form divided along a longitudinal direction at an upper portion (the twelve oclock position) and a lower portion (the six oclock position) as shown in FIG. 3. 0048 For example, the nacelle 14 h

44、as a right side portion 14R and a left side portion 14L. The right side portion 14R and the left side portion 14L are supported on the pylon 40 by a hinge portion (not shown) that is located at the upper por tion. The right side portion 14R and the left side portion 14L are turned outward about the

45、hinge portion at the time of maintenance.0049 A right side portion 15R and a left side portion 15L of the core cowl 15 are similarly configured.0050 The engine accessories, and pipes, lines, sensors, valves, actuators etc. accompanying the engine accessories (referred to as accessories below) are ar

46、ranged in a fire com partment between the engine case 121 and the core cowl 15, in outfitting spaces Sl and S2 respectively formed between the right side portions 14R and 15R and the left side portions 14L and 15L each having an arc shape in section, and in a pylon body 41.0051 The outfitting spaces

47、 Sl and S2 are formed continu ously from a front end to a rear end of the core cowl 15. 0052 An upper region of the bypass flow path18 is used as the upper outfitting space Sl in which the accessories are arranged. A lower region of the bypass flow path 18 is used as the lower outfitting space S2 in

48、 which the accessories are arranged.0053 By collectively installing the accessories in the upper outfitting space Sl or the lower outfitting space S2, a region in which the fan flow is disturbed by the accessories is limited to the upper region and the lower region of the bypass flow path 18.0054 In

49、 the present embodiment, the ratio of the diameter of the engine body 12 to the diameterof the nacelle 14 is large, and the dianieter of the nacelle 14 cannot be increased due to limitations on ground clearance. Thus, an interval between the inner periphery of the nacelle 14 and the outer periphery

50、of the core cowl 15 is small. Therefore, the bypass flow path 18 has a small radial dimension (height).0055 To ensure a flow path sectional area meeting required thrust even when the bypass flow path 18 is radially narrow as described above, circumferential dimensions3 (widths) of the outfitting spa

51、ces Sl and S2 in which the accessories are arranged are set as small as possible.0056 Although the width of the upper outfitting space Sl and the width of the lower outfitting space S2 do not need to be the same, both of the widths of the outfitting spaces Sl and S2 are preferably set to required mi

52、nimum values.0057 The pylon 40 used for supporting the turbofan engine 10 on the main wing 11 includes the pylon body 41 that is a primary structural member, and a fairing 42 that covers the pylon body 41 as shown in FIG. 1.0058 The pylon body 41 is formed in a box-like shape having a rectangular sh

53、ape in section, and longitudinally extends.0059 A lower portion of the pylon body 41 faces the upper outfitting space Sl as shown in FIG. 3.0060 Here, the pylon body 41 serves as resistance against the fan flow flowing through a region around the upper out fitting space Sl. Thus, to obtain required

54、thrust, a circumfer ential dimension (width) of the pylon body 41 is set as small as possible.0061 The width of the pylon body 41 may be equal to or different from the width of the upper outfitting space Sl, and is preferably set to a required minimum value.0062 In some cases, the accessories such a

55、s the engine oil cooler 43 and the precooler 44 are arranged within the pylon body. However, an inner portion of the pylon body 41 of the present embodiment does not have a volume large enough to arrange the accessories therein due to the small width. 0063 In the present embodiment, the engine oil cooler 43 and the precooler 44 are suspended from a lo