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US 2013/0009004A1 Jan.10,2013 [0019] InFIG.1B,afrontperspectivevieWofpropulsion thebottomedgeofbox36,box36isattachedtoduct28 system 12A broken out of internal propulsion aircraft 10 along line 1B in FIG. 1A is shoWn, With propulsion system 12A having thrust reverser 14A in the deployed position. ShoWn inFIG. 1B arepropulsionsystem 12A, thrustreverser 14A, intake inlet22A, exhaust outlet24A, propulsion system duct28,fan30,gasturbineengine32,kickerblocker34,box 36, airA, bypass airAB, primary airAP, and exhaust gas G. While propulsion systems 12A-12D may not be identical, for thepresentpurposespropulsionsystem12Aisrepresentative ofpropulsionsystems12A-12D. [0020] Propulsionsystem12Aissituatedinpropulsion systemduct28,Withintakeinlet22A atthefrontofduct28 andexhaustoutlet24A attherearofduct28.Behindintake inlet22A isfan30.Fan30isconnectedtogasturbineengine 32, Which is also situated in duct 28. BetWeen gas turbine engine32andexhaustoutlet24A isthrustreverser14A. [0021] Thrustreverser14Aincludeskickerblocker34and box 36.Intheillustratedembodiment, thrustreverser14A is in the deployed position. Therefore, kicker blocker 34 is positionedpartiallyinduct28andbox36,andpartiallyoutof duct28andbox36.When propulsionsystem14A isinstalled in aircraft 10 (shoWn in FIG. 1A), box 36 extends betWeen duct 28 and fuselage 16 (shoWn in FIG. 1A). [0022] Duringoperationofpropulsionsystem12A,With thrustreverser14Abeingdeployed,airA entersintakeinlet 22A.AirAisthendividedintobypassairAB andprimaryair AP. Primary airAP enters gas turbine engine 32 Where itis used in a combustion process to accelerate primary airAP rearWard and provide rotational force. The rotational force is usedtoturnfan30.Fan30acceleratesbypassairABrearWard. Aftergasturbineengine32,primaryairAPandbypassairAB combinetoformexhaustgasG.ExhaustgasG hasasigni? cant amount of momentum and produces thrust When exhausted to the atmosphere. Because thrust reverser 14A is deployed, exhaust gas G exits propulsion system 12A at an upWardandforWardangle. [0023] Thecomponentsandcon?gurationofpropulsion system 12A as shoWn in FIG. 1B alloW for thrust to be generated to poWer aircraft 10 While concealing fan 30 and gasturbineengine32fromradardetection.Inaddition,thrust reverser14AalloWsforbothprimaryairAPandbypassairAB toberedirectedforWardandupWard,Whichgeneratesareac tionary force in the doWnWard and rearWard directions on aircraft 10 (shoWn in FIG. 1). aroundanapertureinduct28.Alongthetopedgeofbox36is box seal 44, Wherein box seal 44 is a ?nger seal that has tWo substantially ?at portions, With one of the surfaces being connectedtobox 36,andathirdportionthatextendsbetWeen an edge of each of the ?at portions (to generally form a “C” shape).Box seal44contactsfuselage16topreventleakageof exhaustgasG betWeenpropulsionsystemduct28andfuse lage16. [0027] Kickerblocker34isasinglecomponentthatcanbe divided into tWo sections that have a junction along portion division 50 With the loWer section being blocker portion 46 andtheuppersectionbeingkickerportion48.Kickerblocker 34 is rotatably connected to hinge 42 at portion division 50. When thrust reverser 14A is in the deployed position (as shoWn in FIG. 2), blocker portion 46 extends into duct 28 substantially across the entire Width and the entire height of duct 28. Also When deployed, kicker portion 48 ispositioned partially in box 36 and extends past box seal 44. Thereby, kickerportion48extendsbeyondfuselage16(shoWninFIG. 1A). [0028] Duringoperationofpropulsionsystem12AWith thrust reverser 14A in the deployed position, exhaust gas G that is traveling through duct 28 encounters blocker portion 46 of kicker blocker 34 prior to exiting propulsion system 12A through exhaust outlet 24A. Kicker blocker 34 then redirectsexhaustgasG upWardsandforWardsthroughbox 36. At the outermost end of kicker blocker 34, kicker portion 48iscurvedfartherforwardthantherestofkickerportion48 alongsubstantiallytheentireWidthofkickerportion48.The compoundshapeofkickerportion48directsexhaustgasG in a more forWard direction than if kicker portion 48 Were straight,andkickerportion48doessoaftergashasexitedbox 36. [0029] BecauseexhaustgasGisbeingexhaustedfromfan 30 and gas turbine engine 32 (both shoWn in FIG. 1B), exhaustgasG istravelingathighvelocity.When exhaustgas G isredirectedbykickerblocker34,exhaustgasG exertsa substantial amount of force on kickerblocker 34. This force is transmittedthroughhinge42,tosupportrails40,andisdis sipatedinfuselage16(shoWninFIG.1A). [0030] BecauseexhaustgasG includesprimaryairAP (shoWn in FIG. 1B), exhaust gas G has a high temperature. Because kicker blocker 34 is exposed to hot exhaust gas G, kicker blocker 34 is comprised of material that is able to Withstandsuchheatand stilretainitsstrength.Inaddition, thematerialiscorrosionresistant.Suchmaterialincludes,but is not limited to, 600 alloy steel, 625 alloy steel, 718 alloy stel,titanium,stainlessstel,andceramicmatrixcomposite. Furthermore, kicker blocker 34 can have a thermal barrier coating to further prevent failure due to exposure to hot exhaustgasG.Thisthermalbarriercoatingmay beappliedto kicker blocker 34, or to only a section of kicker blocker 34, such as blocker portion 46. [0024] InFIG.2,afrontperspectivevieWoftWothrust reversers14inthedeployedpositionisshoWn.ShoWninFIG. 2 are thrust reverser 14A, exhaust outlet 24A, propulsion system duct 28, kicker blocker 34, box 36, rear box side 37, lateral box sides 38, box ramp 39, support rails 40, hinge 42, box seal 44, blocker portion 46, kicker portion 48, portion division 50, and exhaust gas G. While thrust reversers 14A 14D may not be identical, for the present purposes thrust reverser14A isrepresentativeofthrustreversers14A-14D. [0025] Supportrails40surroundpropulsionsystemduct28 and are connected to fuselage 16 (shoWn in FIG. 1A). Attached to support rails 40 is hinge 42. Support rails 40 provide an interface betWeen hinge 42 and fuselage 16 that is capable oftransmitting force from hinge 42 to fuselage 16. [0026] Intheillustratedembodiment,box36hasfoursides, box36andWithoutdeformingordestroyingkickerblocker With the rear box side 37 being attached to hinge 42. Extend ingforWardfromtheoppositeends ofrearbox side37 are lateral box sides 38. Extending betWeen lateral box sides 38 and spaced apart from rear box side 37 isbox ramp 39. Along 34. That is due in part to the fact that the reactionary force on thrustreverser14istransmittedthroughhinge42andsupport rails 40 and is dissipated throughout fuselage 16 (shoWn in FIG. 1A). [0031] The components and con?guration of thrust reverser14asshoWninFIG.2alloWforexhaustgasG tobe usedtoproducereversethrustforaircraft10.More speci? cally, this occurs Without placing undue stress on duct 28 orPDF Image | INTERNAL GAS TURBINE PROPULSION THRUST REVERSER
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