3-筛选及标引后的专利著录项目数据及专利全文us8720183b2_W

1、US008720183B2(12) United States Patent(io) Patent No.:US 8,720,183 B2Welch et al.(45) Date of Patent:May 13,2014(54)THRUSTREVERSER TRANSLATING(56)References Cited SLEEVE ASSEMBLYU.S. PATENT DOCUMENTS(75)Inventors: John Michael Welch, Wichita, KS (US);4,585,189 A * 4/1986 Buxton244/54Christopher Stev

2、en Sawyer, Udall, KS4,629,146 A * 12/1986 Lymons244/53 R(US)4,679,750 A *7/1987 Burhans244/129.44,697,763 A * 10/1987 Vermilye244/129.45,350,136 A *9/1994 Prosser et al244/129.4(73) Assignee: Spirit AeroSystems, Inc., Wichita, KS5,778,659 A *7/1998 Duesler et al60/226.1(US)6,592,074 B2 *7/2003 Dehu

3、et al244/110 B8,505,307 B2 *8/2013 Wang60/7712010/0050596 A l*3/2010 W inter et al60/226.3(* )Notice:Subject to any disclaimer, the term of this2010/0064660 A l*3/2010 Vauchel et al60/226.2patent is extended or adjusted under 352010/0218480 A l*9/2010 Vauchel et al60/226.2U.S.C. 154(b) by 738 days.2

4、011/0120079 A l*5/2011 Schwark et al60/226.22013/0091825 A l*4/2013 Joret et al60/226.2(21)Appl. No.: 13/038,621* cited by examinerPrimary Examiner William H Rodriguez(22) Filed:Mar. 2, 2011(74) Attorney, Agent, or Firm Hovey Williams LLP(57)ABSTRACT(65)Prior Publication DataA translating sleeve ass

5、embly for use with an aircraft engine US 2013/0075492 AlMar. 28, 2013thrust reverser broadly comprises a slider track, a lifting bolt,and a hinge. The slider track may include a tubular sidewalland a guide channel formed therein that follows a curved path(51) Int. Cl.along a length thereof. The lift

6、ing bolt may be slidably posiF02K3/02(2006.01)tioned within the slider track. The hinge may include a firstF02K 1/76(2006.01)hinge element with a base coupled to an outer cowl shroud, a(52) U.S. Cl.second hinge element with a hinge rod slidably positionedCPC F02K1/763 (2013.01); F 02K 1/766 (2013.01

7、) within the guide channel, and a pin about which the first hingeelement and the second hinge elementpivot. During deployUSPC . 60/226.2; 244/110 B; 244/129.4ment of the thrust reverser, the lifting bolt slides aftward and(58) Field of Classification Searchthe hinge rod slides within the guide chann

8、el, urging the CPCF02K 1/763; F02K 1/766 lifting bolt to pivot and the hinge to open, thereby lifting theUSPC . 60/226.2, 226.3; 244/110 B, 129.4outer cowl shroud away from the center of the aircraftengine.See application file for complete search history.15 Claims, 6 Drawing SheetsU.S. PatentMay 13,

9、 2014Sheet 1 of 6US 8,720,183 B210U.S. PatentMay 13, 2014Sheet 2 of 6US 8,720,183 B2U.S. PatentMay 13, 2014Sheet 3 of 6US 8,720,183 B2U.S. PatentMay 13, 2014Sheet 5 of 6US 8,720,183 B25fig . 6U.S. PatentMay 13, 2014Sheet 6 of 6US 8,720,183 B232US 8,720,183 B212THRUST REVERSER TRANSLATINGlating aftwa

10、rd. The second translating sleeve assembly may SLEEVE ASSEMBLYinclude a secondhinge coupled to the secondupper portion of the second inner surface. The second hinge may be operableBACKGROUND OF THE INVENTIONto openwhile translating aftward. The third translating sleeve5 assembly may include a third

11、hinge coupled to the first lower1. Field of the Inventionportion of the first inner surface. The third hinge may be Embodiments of the present invention relate to aircraftoperable to open while translating aftward. The fourth trans engine thrust reversers. More particularly, embodiments oflating sle

12、eve assembly may include a fourth hinge coupled to the present invention relate to aircraft engine thrust reversersthe second lower portion of the second inner surface. The with translating and lifting sleeve assemblies.10 fourth hinge may be operable to open while translating aft2. Description of t

13、he Related Artward.Aircraft engine thrust reversers may include a plurality ofDuring deployment of the thrust reverser, the left outer cascade elements positioned along an outer perimeter of an cowl shroud may be pushed aftward along with the first hinge engine. The cascade elements may include an a

14、rray of open and the third hinge, thereby opening the first hinge and the ings, wherein at least one wall of each opening is curved 15 third hinge such that the left outer cowl shroud is lifted away forward with respect to the engine. When the thrust reverser is from the center ofthe aircraft engine

15、, and the right outer cowl stowed, the cascade elements are covered by an outer cowl shroud may be pushed aftward along with the second hinge shroud. During deployment of the thrust reverser, the outer and the fourth hinge, thereby opening the second hinge and cowl shroud is translated aftward and a

16、 portion of the airflow the fourth hinge such that the right outer cowl shroud is lifted through the engine is directed through the openings of the 20 away from the center of the aircraft engine.cascade elements to provide reverse thrust. Occasionally, theThis summary is provided to introduce a sele

17、ction ofconouter cowl shroud may not fully clear the cascade elements, cepts in a simplified form that are further described below in resulting in less than optimal reverse thrust. Additionally, the the detailed description. This summary is not intended to translating sleeve is usually composed of a

18、n acoustic fan duct identify key features or essential features of the claimed sub element and an outer cowl aerodynamic element, both of 25 ject matter, nor is it intended to be used to limit the scope of which have to translate over a significant stroke distance to the claimed subject matter.expos

19、e the cascade elements for reverse thrust.Other aspects and advantages of the present invention willbe apparent from the following detailed description of the SUMMARY OF THE INVENTIONembodiments and the accompanying drawing figures.30Embodiments of the present invention solve the above-BRIEF DESCRIP

20、TION OF THE DRAWING mentioned problems and provide a distinct advance in the artFIGURESof aircraft engine thrust reversers. More particularly, embodiments ofthe invention provide a translating set assembly forEmbodiments of the present invention are described in use with an aircraft engine thrust re

21、verser that lifts an outer 35 detail below with reference to the attached drawing figures, cowl shroud away from the engine as the outer cowl shroud wherein:translates aftward.FIG. li sa side view of an under-wing aircraftengine;An embodiment ofthe translating sleeve assembly broadlyFIG. 2 is a sect

22、ional view of at least a portion of an aircraft comprises a slider track, a lifting bolt, and a hinge. The slider engine thrust reverser in the stowed position;track may include a tubular sidewall with a guide channel 40 FIG. 3 is a sectional view of at least a portion of the aircraft formed therein

23、 that follows a curved path along the length engine thrust reverser in the deployed position;thereof. The lifting bolt is slidably positionedwithin the sliderFIG. 4 is a perspective exploded view of a translating track. The hinge may include a first hinge element with a base sleeve assembly construc

24、ted in accordance with various coupled to an outer cowl shroud, a second hinge element with embodiments of the present invention;a hinge rod slidably positioned within the guide channel and 45 FIG. 5 is a perspective view of an aircraft engine nacellecoupled to the lifting bolt, and a pin about whic

25、h the first showing at least a portion of the thrust reverser in the stowed hinge element and the second hinge element pivot.position;During deployment of the thrust reverser, the outer cowlFIG. 6 is a perspective view of the aircraft engine nacelle shroud may be pushed aftward such that the lifting

26、 bolt slides showing at least a portion of the thrust reverser in the within the slider track and the hinge rod slides within the 50 deployed position;guide channel, urging the lifting bolt to pivot and the hinge toFIG. 7 is a rear view of the aircraft engine nacelle showing open, thereby lifting th

27、e outer cowl shroud away from the at least a portion of the thrust reverser in the deployed posi center of the aircraft engine. In this embodiment, only the tion; andouter aerodynamic cowl has to be translated aft to expose theFIG. 8 is a fragmentary perspective view of the aircraftcascades for reve

28、rse thrust, and the stroke length is signifi 55 engine nacelle showing a close-up of one of thetranslating cantly shorter.sleeve assemblies.Other embodiments of the present invention may includeThe drawing figures do not limit the present invention to an aircraft engine thrust reverser broadly compr

29、ising a left the specific embodiments disclosed and described herein. The outer cowl shroud, a right outer cowl shroud, and first, second, drawings are not necessarily to scale, emphasis instead being third, and fourth translating sleeve assemblies. The left outer 60 placed upon clearly illustrating

30、 the principles of the inven cowl shroud may include a first inner surface, a first lower tion.portion, and a first upper portion. The right outer cowl shroudmay include a second inner surface, a secondlower portion,DETAILED DESCRIPTION OF THE and a second upper portion.EMBODIMENTSThe first translat

31、ing sleeve assembly may include a first 65hinge coupled to the first upper portion of the first innerThe following detailed description of the invention refer surface. The first hinge may be operable to open while trans- ences the accompanying drawings that illustrate specificUS 8,720,183 B234embodi

32、ments in which the invention can be practiced. The portion of the outer cowl shroud 28 is covering the cascade embodiments are intended to describe aspects of the inven elements 26. When the thrust reverser 16 is deployed, the tion in sufficient detail to enable those skilled in the art to outer cow

33、l shroud 28 may move aftward, as discussed inmore practice the invention. Other embodiments can be utilized and detail below, to expose the cascade elements 26 and allow an changes can be made without departing from the scope of the 5 airflow path through the cascade elements 26.present invention. T

34、he following detailed description is,The actuating units 30 may include an actuator (not shown therefore, not to be taken in a limiting sense. The scope of thein the figures) and an actuator arm 50, seen in FIGS. 2-3. present invention is defined only by the appended claims,There may be at least fou

35、r actuating units 30 located around along with the full scope of equivalents to which such claimsthe circumference of the engine 10. With eachactuating unit are entitled.10 30, the actuator may be positioned forward of the cascade In this description, references to “one embodiment”, “anelements 26 a

36、nd may be powered electrically, hydraulically,embodiment”, or “embodiments” mean that the feature or or the like. The actuator arm 50 may be coupled to an output features being referred to are included in at least one embodi of the actuator and may extend aftward to couple with the ment of the techn

37、ology. Separate references to “one embodi outer cowl shroud 28 through a push ring 52 and a shroudment”, “an embodiment”, or “embodiments” in this descrip 15 attach fitting 54.tion do not necessarily refer to the same embodiment and areThe push ring 52 may be of a circular or disk shape and may also

38、 not mutually exclusive unless so stated and/or except as be positioned around the circumference of the engine 10 will be readily apparent to those skilled in the art from the inward from the cascade elements 26. The push ring 52 may description. For example, a feature, structure, act, etc. be attac

39、hed in multiple locations (four, in various embodi described in one embodiment may also be included in other 20 ments) to the aft end of each actuator arm 50 and may further embodiments, but is not necessarily included. Thus, the couple to the shroud attach fittings 54.present technology can include

40、 a variety of combinationsThe shroud attach fitting 54 may include mechanical fas and/or integrations of the embodiments described herein.tening components that couple the push ring 52 to the outer An under-wing aircraft engine 10, shown in FIG. 1, maycowl shroud 28. In various embodiments, there ma

41、y be four include a nacelle 12 that covers and protects the internal 25 shroud attach fittings 54a first shroud attach fitting 54 posi engine 10 components. The engine 10 may further include ationed on the inner surface 48 of the upper portion near the plurality of support beams 14, as shown in FIG.

42、 7, and a thrustforward edge of the right outer cowl shroud 44, a second reverser 16, as shown in FIGS. 2-3. The support beams 14shroud attach fitting 54 positioned on the inner surface 48 of may include an upper left support beam 18, an upper rightthe lowerportion nearthe forward edge ofthe right o

43、uter cowl support beam 20, a lower left support beam 22, and a lower 30 shroud 44, a third shroud attach fitting 54 positioned on the right support beam 24. The support beams 14 extendalong ainner surface 48 of the upper portion near the forward edge of portion of the length of the engine 10 and pro

44、vide somethe left outer cowl shroud 42, and a fourth shroud attach fitting structural framework for the engine 10. The thrust reverser 1654 positioned on the inner surface 48 ofthe lowerportion nearmay be a cascade-type of thrust reverser 16 that includes, the forward edge of the left outer cowl shr

45、oud 42.among other components, a plurality of cascade elements 26, 35The components ofthe translating sleeve assembly 32 may an outer cowl shroud 28, and a plurality of actuating units 30.be best seen in FIG. 4. The slider track 34 may be of an A translating sleeve assembly 32, shown in FIGS. 2-4, a

46、selongated, hollow, generally tubular shape and may include a constructed in accordance with various embodiments of theforward end 56, an aft end 58, a tubular sidewall 60, and a current invention may be used with the thrust reverser 16 andguide channel 62. There may be a gap along the circumfer may

47、 broadly comprise a slider track 34, a lifting bolt 36, and 40 ence of the tubular sidewall 60 that extends the lengthof the a hinge 38.slider track 34 in which the guide channel 62 is formed. The cascade elements 26, best seenin FIGS. 2-3 and 6, mayFurthermore, the guide channel 62 may follow a cur

48、ved path include an array of arcuate vanes 40 that possess a curvaturewhen moving from the forward end 56 ofthe slidertrack 34 to such that the outer edges of the vanes 40 are pointing generthe aft end 58. For example, nearthe forward end 56, the guide ally forward. In some embodiments, multiple cas

49、cade ele 45 channel 62 may be positioned at a first angle with respect to ments 26 may be positioned adjacent one another to form athe central longitudinal axis ofthe slider track 34. Near the aft band along the circumference of the engine 10. In otherend 58, the guide channel 62 may be positioned a

50、t a second embodiments, there may be a single elongated cascade eleangle that is pivoted from the first angle. In various embodi ment located along the circumference of the engine 10. Thements, the guide channel 62 may pivot approximately ninety cascade elements 26 may be covered by the outer cowl s

51、hroud 50 degrees from the forward end 56 to the aft end 58, although28 when the thrust reverser 16 is stowed. During deployment greater or lesser angular rotations are possible.of the thrust reverser 16, the cascade elements 26 generallyThe inner diameter of the slider track 34 may be slightly direc

52、t airflow, exhaust gases, or a combination thereof in alarger than the outer diameter ofthe lifting bolt 36. The lifting forward direction relative to the engine 10.bolt 36 is generally positioned within the tubular sidewall 60 The outer cowl shroud 28, also known as a sleeve, may 55 of the slider t

53、rack 34 such that the hinge rod 80 fits within the include a left outer cowl shroud 42 and a right outer cowlguide channel 62. The lifting bolt 36 may be capable of shroud 44, best seen in FIG. 7, both of which mayhave asliding along the length of the slider track 34. Due to the generally semi-cylin

54、drical shape and, in combination, maycurvature ofthe guide channel 62, the lifting bolt 36 may pivot form an aft portion ofthe nacelle 12 that is separable from theabout the longitudinal axis of the slider track 34 as the liftingrest of the nacelle 12. The left outer cowl shroud 42 and the 60 bolt 3

55、6 slides along the length thereof.right outer cowl shroud 44 may both include an outer surfaceThehinge 38 may include a first hinge element 64, a second 46 and an inner surface 48. In various embodiments, the lefthinge element 66, and a pin 68. Generally, the first hinge outer cowl shroud 42 and the

56、 right outer cowl shroud 44 mayelement 64 includes features that interleave with similar fea be shaped and sized to be roughly symmetric about a centraltures on the second hinge element 66. In various embodi vertical plane.65 ments, the first hinge element 64 may include a plurality of When the thru

57、st reverser 16 is stowed, the outer cowlfirst fingers 70 with first spaces 72 in between. The second shroud 28 may be positioned forwardly, such that at least ahinge element 66 may include a plurality of second fingers 74US 8,720,183 B256with second spaces 76 in between at the same pitch as the firsttranslating the push ring 52 along with the shroud attach fingers 70 and the first spaces 72. The first hinge