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US 2013/0009004 A1 Jan. 10,2013 yet another example, the forces from each thrust reverser 14A-14D istransferredtoahinge42 sothattheforcescanbe dissipatedinfuselage16. [0060] WhiletheinventionhasbeendescribedWithrefer encetoanexemplaryembodiment(s),itWillbeunderstoodby thoseskilledintheartthatvariouschangesmay bemade and equivalents may be substituted for elements thereofWithout departingfromthescopeoftheinvention.Inaddition,many modi?cations may be made to adapt a particular situation or material to the teachings of the invention Without departing fromtheessentialscopethereof.Therefore,itisintendedthat the invention not be limited to the particular embodiment(s) disclosed,butthattheinventionWillincludeallembodiments fallingWithinthescopeoftheappendedclaims. 1. A thrust reverser for a gas turbine engine, the thrust reversercomprising: ahinge; apropulsionsystemductthroughWhichbypassairandgas path air travel, the propulsion system duct having an intake inlet and an exhaust outlet; a kicker blocker that has a kicker portion and a blocker portion, the kicker blocker being rotatably attached to the hinge, the kicker blocker being movable betWeen a stoWedpositionandadeployedposition; Wherein the blocker portion extends into the propulsion system duct When the kicker blocker is in the deployed position to block bypass air and gas path air traveling through the propulsion system duct in a ?rst direction priortotheexhaustoutlet,therebyredirectingthebypass air and the gas path air in a second direction. 2. The thrust reverser of claim 1, Wherein an angle of rotationofthekickerblockerbetWeenthedeployedposition and a horiZontal line ismore than thirty degrees and less than sixtydegrees. 3.Thethrustreverserofclaim1,Whereinthekickerblocker includes a thermal barrier coating. 4. The thrust reverser of claim 1, and further comprising: abox comprising: a?rstsidepositionedalongthelengthofthehinge; a second side extending forWard from a ?rst end of the ?rstside; athirdsideextendingforWardfromthesecondendofthe ?rstside; a fourth side extending betWeen the second and third sides that is offset from the ?rst side, Wherein the fourth side is a ramp that is positioned at an angle morethanthirtydegreesandlessthansixtydegrees. 5. The thrust reverser of claim 4, Wherein a movable por tion of a kicker seal moves to substantially the same angle as thefourthsideofthebox. 6. The thrust reverser of claim 1, and further comprising: alockingmechanismthatmustbeopenedinordertorotate the kicker blocker from the stoWed position to the deployedposition. 7.Thethrustreverserofclaim1,Whereinthekickerblocker isattachedtothehingeatajunctionofthekickerportionand theblockerportion. 8. The thrust reverser of claim 1, and further comprising: an actuator that is connected to the hinge and that exerts force on the kicker blocker to rotate the kicker blocker on the hinge, Wherein the actuator is selected of a type from the group consisting of an electro-mechanical actuator, a hydraulic actuator, a pneumatic actuator, a 9. An internal propulsion aircraft including a thrust reverser,theaircraftcomprising: afuselage; a Wing extending from the fuselage; an internal propulsion system positioned Within a propul sion system duct in one of the fuselage or the Wing, the propulsionsystemcomprising: an intake inlet; a fan; a gas turbine engine; an exhaust outlet; and a thrust reverser positioned betWeen the gas turbine engine and the exhaust outlet of the propulsion sys tem, the thrust reverser being movable betWeen a stoWedpositionandadeployedposition,Whereinthe thrust reverser blocks the propulsion system duct When inthedeployedposition. 10. The aircraft of claim 9, Wherein the thrust reverser furthercomprises: ahinge; a kicker blocker that has a kicker portion and a blocker portion, the kicker blocker being rotatably attached to the hinge, the kicker blocker being movable betWeen a stoWedpositionandadeployedposition; WhereintheblockerportionextendsintotheductWhenthe kicker blocker is in the deployed position to block bypassairandgaspathairtravelingthroughtheductin a?rstdirectionpriortotheexhaustoutlet,therebyredi recting the bypass air and the gas path air in a second direction. 11. The aircraft of claim 10, Wherein the blocker portion andthekickerportionareportionsofaunitarykickerblocker. 12. The aircraft of claim 11, and further comprising: a hinge that is connected to the fuselage and to Which the kickerblockerisrotatablyconnected. 13.Theaircraftofclaim11,Whereinaportionofthekicker portion is curved substantially across a Width of the kicker portion. 14. The aircraft of claim 10, and further comprising: aboxthatextendsbetWeenthepropulsionsystemductand thefuselage,thekickerportionbeingpositionedinthe box When thethrustreverserisdeployed. 15. The aircraft of claim 14, and further comprising: a box seal positioned betWeen the box and the fuselage. 16. The aircraft of claim 14, Wherein the box includes a kicker seal that contacts the kicker portion When the thrust reverser is in the stoWed position. 17. The aircraft of claim 14, and further comprising: a transition feature of the propulsion system duct that is substantially curved Where the box connects to the pro pulsionsystemduct. 18. The aircraft of claim 10, and further comprising: a locking mechanism that must be unlocked in order to rotatethekickerblockerfromthestoWedpositiontothe deployedposition. 19. The aircraft of claim 10, Wherein the blocker portion includes a thermal barrier coating. 20. The aircraft of claim 10, Wherein the blocker portion extends across substantially an entire Width and an entire heightofthepropulsionsystemductWhenthethrustreverser isdeployed. cable,andaWorm gear.PDF Image | INTERNAL GAS TURBINE PROPULSION THRUST REVERSER
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