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US 2013/0009004 A1 Jan. 10,2013 [0032] InFIG.3A,across-sectionvieWalongline3-3in [0038] Thecomponentsandconnectionsofthrustreverser FIG. 2 ofthrustreverser 14A inthe stowed position isshown. ShoWn inFIG. 3A arethrustreverser14A, fuselage16,pro pulsion system duct 28, kicker blocker 34, box 36, box ramp 39, support rails 40, hinge 42, blocker portion 46, kicker portion48,actuator60,transitionfeature62,kickerseal64, atangle61.Preferably,angle61isatleastthirtydegreesand andexhaustgasG.As statedpreviously,Whilethrustreversers 14A-14Dmaynotbeidentical,forthepresentpurposesthrust reverser14A isrepresentativeofthrustreversers14A-14D. [0033] Thecomponentsandconnectionsofthrustreverser 14A are as described previously in FIGS. 1A-2, With addi tional detail presently shoWn. For example, actuator 60 is rotatably attached to kicker blocker 34 at one end and extends throughanapertureinrearboxside37.Actuator60isrotat ablyattachedtokickerblocker34attheoppositeend.Inthe [0039] Asstatedpreviously,Whenthrustreverser14Ais illustrated embodiment actuator 60 is a linear actuator of the fully deployed, blocker portion 46 extends into duct 28 sub double-actingpneumaticcylindertypethatpushesonkicker stantiallyacrosstheentireWidthandtheentireheightofduct blocker 34 to put thrust reverser 14A in the stoWed position. Conversely, actuator 60 pulls kicker blocker 34 to put thrust reverser14A inthedeployedposition.Inaddition,actuator60 is offset from the center of hinge 42 such that actuator 60 has leverage With Which to act on kicker blocker 34. The reac tionaryloadfromactuator60exertingforceonkickerblocker pastkickerblocker34. 34 is transmitted to hinge 42, Which is connected to fuselage 16throughsupportrails40. 12A,theamountofareaavailableforexhaustgasG toHow [0034] Nearboxramp39,duct28hastransitionfeature62. throughthatiscreatedbythedeploymentofkickerportion48 Duct 28 also has kicker seal 64 that is attached to transition feature 62. Kicker seal 64 is comprised of a ?exible metal suchas,butnotlimitedto,718nickelsteelortitanium.When in the stoWed position, kicker portion 48 covers the aperture in duct 28 and rests on kicker seal 64. Kicker seal 64 contacts kicker portion 48 along substantially the entire Width of kicker portion 48 and substantially prevents leakage from duct 28 into box 36 along that edge. In addition, blocker portion 46 is positioned substantially alongside duct 28 Withinduct28.Thereby,blockerportion46doesnotsubstan tially obstruct duct 28 When in the stoWed position [0035] The components and con?guration of thrust reverser 14A as shoWn in FIG. 3A alloW for thrust reverser 14A to be moved betWeen the stoWed position and the deployed position. In addition, When thrust reverser 14A is stoWed,exhaustgasG isalloWedtotravelthroughduct28in a generally rearWard direction Without being substantially impeded by blocker portion 46 and Without substantially leakingintoduct28. is at least as large as the amount of area eliminated by blocker portion 46. Preferably, the amount of area created is greater thantheamount ofareaeliminated. [0041] Asstatedpreviously,nearboxramp39,duct28has transitionfeature 62. Because box ramp 39 isatan acute angle to duct 28, transition feature 62 has a curved radial face. In addition, because the aperture in duct 28 is rectilinear, tran sition feature 62 curves circumferentially With duct 28. Thereby, transition feature 62 smoothes the transition that exhaustgasG mustmakebetWeentravelinggenerallyrear Ward through duct 28 and traveling generally forWard and upWardthroughbox36. [0042] ToassistWithdirectingexhaustgasGforWardsand upWards, box ramp 39 is positioned at angle 63. Preferably, angle 63 is at least thirty degrees and is not more than sixty degreesfromhoriZontal(Whenaircraft10,shoWninFIG.1A, is on the ground). More preferably, angle 63 is at least forty degrees and is not more than ?fty degrees from horiZontal. While the angle 63 iscan be the same as angle 61, angle 63 is [0036] DepictedinFIG.3Aisoneembodimentofthe canbedifferentfromangle61. present invention, to Which there are alternative embodi ments. For example, actuator 60 can be one ofmany types of actuators. More speci?cally, actuator 60 can be, but is not limitedto,anoilhydrauliccylinder,afuelhydrauliccylinder, an electro-mechanical actuator, a cable actuator, and a rotary driveractuatorhavingaWorm gear(shoWninFIG.4B).For another example, kicker blocker 34 can be offset from hinge 42 to provide leverage for actuator 60. [0043] TocreateasmoothertransitionbetWeentransition feature 62 and box ramp 39, kicker seal 64 can rotate to form acomplimentaryangleWiththatofboxramp 39.Thisoccurs oncekickerportion48 isrotatedoffofkickerseal64.When kickerportion48isrotatedasu?icientamount,kickerseal64 Will rotate to its natural resting angle Which is angle 62. Preferably,angle62isatleastthirtydegreesandisnotmore thansixtydegreesfromhoriZontal(Whenaircraft10,shoWn in FIG. 1A, is on the ground). More preferably, angle 62 is at least forty degrees and is not more than ?fty degrees from horiZontal. While the angle 62 is can be the same as angle 61 [0037] InFIG.3B,across-sectionvieWalongline3-3in FIG.2ofthrustreverser14inthedeployedpositionisshoWn. ShoWn in FIG. 3B are thrust reverser 14A, fuselage 16, pro pulsionsystemduct28,kickerblocker34,box36,boxramp orangle63,angle62iscanbedifferentfromangle61orangle 39, support rails 40, hinge 42, blocker portion 46, kicker portion48,actuator60,transitionfeature62,kickerseal64, exhaust gas G, angle 61, angle 62, and angle 63. As stated previously,Whilethrustreversers14A-14D may notbeiden tical,forthepresentpurposesthrustreverser14Aisrepresen tative of thrust reversers 14A-14D. 63. [0044] The components and con?guration of thrust reverser 14A as shoWn in FIG. 3B alloW for an adjustable amountofrearWardanddoWnWardthrusttobegeneratedfor aircraft10 (shoWninFIG. 1A).Thisredirectionofthrustis accomplished Without adversely affecting the operation of 14A are as described previously in FIGS. 1A-3A, With addi tional detail presently shoWn. For example, When kicker blocker 34 is fully deployed, the straight section of kicker portion 48 adjacent to portion division 50 (shoWn in FIG. 2) is isnotmorethansixtydegreesfromhoriZontal(Whenaircraft 10, shoWn inFIG. 1A, ison theground). More preferably, angle 61 is at least forty degrees and is not more than ?fty degrees from horiZontal. Thrust reverser 14A can also be partially deployed Wherein the angle of rotation of kicker blocker 34 is less than angle 61. In such a situation, some of exhaustgasG passesthroughduct28andtherestofexhaust gasG isredirectedthroughbox36. 28.Inthefullydeployedposition,blockerportion46blocks at least seventy percent of the thrust generated by propulsion system12A (shoWninFIG. 1B),Withthirtypercentleakage pastkickerblocker34.Preferably,blockerportion46blocks atleastninetypercentofthethrust,Withtenpercentleakage [0040] InordertopreventstallingofpropulsionsystemPDF Image | INTERNAL GAS TURBINE PROPULSION THRUST REVERSER
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